Navy NAVY Proposal Submission The responsibility for the

NAVY
Proposal Submission
The responsibility for the implementation, administration and management of the Navy SBIR program is with the
Office of the Chief of Naval Research. The Navy SBIR Program Manager is Mr. Vincent D. Schaper. Inquiries of
a general nature may be brought to the Navy SBIR Program Manager's attention and should be addressed to:
Office of the Chief of Naval Research
ATTN: Mr. Vincent D. Schaper
800 North Quincy Street, BCT #1, Room 922
Arlington, VA 22217-5000
(703) 696-4286
SBIR proposals shall not be submitted to the above address and must be received by the cognizant activities listed
on the following pages in order to be considered during the selection process.
The Navy's mission is to maintain the freedom of the open seas. To that end the Navy employs and maintains air,
land and ocean going vehicles and personnel necessary to accomplish this mission. The topics on the following
pages represent a portion of the problems encountered by the Navy in order to fulfill its mission.
The Navy has identified 82 technical topics in this second annual DOD Solicitation to which small R&D businesses
may respond. This is approximately the same amount of topics normally identified by the Navy in the typical May
DOD SBIR solicitation. The reduction of the total amount of topics is a reflection of the funding reduction the
Navy has incurred in FY 1991/FY 1992 and expects similar funding constraints in FY 1992 and beyond. While the
reduction in funds will not impact the Phase I awards that result from the topics listed in this solicitation, it makes it
extremely important that Phase I award recipients influence the end uses of the technology since Phase II SBIR
funds will be limited and thus highly competitive.
Selection of proposals for funding is based upon technical merit and the evaluation criteria contained in this
solicitation document. Because funding is limited the Navy reserves the right to limit the amount of awards funded
under any topic and only those proposals considered to be of superior quality will be funded.
Navy-1
NAVY SMALL BUSINESS INNOVATION RESEARCH PROGRAM
Submitting Proposals on Navy Topics
Phase I proposal (5 copies) should be addressed to:
Administrative
Topic Nos. N92-107 through N92-114 SBIR Contact
Mail/Handcarry Address:
Office of Naval Research Dr. Donald Polk
Attn: ONR Code 11SP, Room 804 (703) 696-4103
SBIR Program, Topic No. N92-______
800 N. Quincy Street, BCT #1
Arlington, VA 22217-5000
Topic Nos. N92-115 through N92-167
Mail Address:
Commander Mr. John Johnson
Naval Air Systems Command (703) 692-7393
Attn: Code AIR-05TE4, SBIR Program, Topic No. N92-______
Washington, DC 20361
Handcarry Address:
Commander
Naval Air Systems Command
Attn: Code AIR-05TE4, SBIR Program, Topic No. N92-______
1411 Jefferson Davis Highway
Jefferson Plaza #1, Room 444
Arlington, VA 22202
Topic Nos. N92-168 and N92-169
Mail Address:
Commander Mr. Donald Wilson
Naval Surface Warfare Center (301) 394-1279
White Oak Laboratory
Attn: Code R-05, SBIR Program, Topic No. N92-______
Silver Spring, MD 20903-5000
Handcarry Address:
Commander
Naval Surface Warfare Center
White Oak Laboratory
Attn: Code R-05, SBIR Program, Topic No. N92-______
Bldg. #1, Reception Room
Silver Spring, MD 20910
Navy-2
Administrative
Topic Nos. N92-170 through N92-174 SBIR Contact
Mail Address:
Commanding Officer Ms. Carol Van Wyk
Naval Air Warfare Center (215) 441-2375
Aircraft Division
Attn: Code 094, SBIR Program, Topic No. N92______
Warminster, PA 18974-5000
Handcarry Address:
Commanding Officer
Naval Air Warfare Center
Aircraft Division
Attn: Code 094, SBIR Program, Topic No. N92-______
Street Road/Jacksonville Road
Warminster, PA 18974-5000
Topic No. N92-175
Mail Address:
Commanding Officer Mr. Pete O'Donnel
Naval Air Warfare Center (908) 323-7566
Aircraft Division Lakehurst
Attn: Code 02T (POD), SBIR Program, Topic No. N92-______
Lakehurst, NJ 08733-5000
Handcarry Address:
Commanding Officer
Naval Air Warfare Center
Aircraft Division Lakehurst
Attn: Code 02T (POD), SBIR Program, Topic No. N92-______
Bldg. #342
Lakehurst, NJ 07833-5000
Topic Nos. N92-176 through N92-179
Mail Address:
Commanding Officer Mr. Robert Dobrowolski
Naval Air Warfare Center (609) 538-6754
Aircraft Division Trenton
Attn: Code PE 34, SBIR Program, Topic No. N92-______
Trenton, NJ 08628-0176
Navy-3
Administrative
Handcarry Address: SBIR Contact
Commanding Officer
Naval Air Warfare Center
Aircraft Division Trenton
Attn: Code PE 34, SBIR Program, Topic No. N92-______
P.O. Box 7176
Trenton, NJ 08628-0176
Topic Nos. N92-180 through N92-183
Mail Address:
Commander Mr. Daniel Watters
Naval Air Warfare Center (301) 863-1144
Aircraft Division
Attn: Code CT222, SBIR Program, Topic No. N92-______
Patuxent River, MD 20670-5304
Handcarry Address:
Commander
Naval Air Warfare Center
Aircraft Division
Attn: Code CT222, SBIR Program, Topic No. N92-______
Bldg. #304
Patuxent River, MD 20670-5304
Topic Nos. N92-184 through N92-186
Mail Address:
Commander Ms. Lois Herrington
Naval Air Warfare Center (619) 939-2712
Weapons Division
Attn: Code 004 (C002), SBIR Program, Topic No. N92-______
China Lake, CA 93555-6001
Handcarry Address:
Commander
Naval Warfare Center
Weapons Division
Attn: Code 004 (C002), SBIR Program, Topic No. N92-______
515 Blandy Avenue, Annex A1
China Lake, CA 93555-6001
Navy-4
Administrative
Topic Nos. N92-187 and N92-188 SBIR Contact
Mail Address:
Commander Mr. Eugene Patno
Naval Air Warfare Center (805) 989-8801
Weapons Division
Attn: Code 3006, SBIR Program, Topic No. N92-______
Point Mugu, CA 93042-5000
Handcarry Address:
Commander
Naval Air Warfare Center
Weapons Division
Attn: Code 3006, SBIR Program, Topic No. N92-______
Bldg. 50, Room 1092
Point Mugu, CA 93042-5000
Navy-5
SUBJECT/WORD INDEX TO THE NAVY SBIR 92.2 SOLICITATION
SUBJECT/WORD TOPIC NO.
ABAQUS...................................................................................................................................................................184
accelerators ................................................................................................................................................................185
acoustic ......................................................................................................................................110, 114, 126, 127, 150
Acoustics ...........................................................................................................................................................114, 126
ACT ...................................................................................................................................................................134, 175
Active Control ...........................................................................................................................................................173
actuator ......................................................................................................................................................................174
Advanced Concepts ...................................................................................................................................................133
agent ..........................................................................................................................................................................139
AI.......................................................................................................................................................................158, 183
Air ASW ...................................................................................................................................................................127
Airborne Instrumentation ..........................................................................................................................................181
Aircrew..............................................................................................................................121, 151, 152, 158, 159, 165
Airflow ..............................................................................................................................................................148, 178
Airflow Instrumentation ............................................................................................................................................178
airframe......................................................................................................................................................151, 152, 164
algorithm....................................................................................................................................................108, 150, 153
algorithms ..................................................................................................113, 119, 126, 149, 150, 153, 159, 169, 172
Amphibious ...............................................................................................................................................................129
Anechoic Chambers...................................................................................................................................................180
antenna.......................................................................................................................................................................180
antennas .....................................................................................................................................................................180
Anthropometric..........................................................................................................................................................161
Application Equipment..............................................................................................................................................139
architecture ................................................................................................................108, 113, 153, 157, 158, 169, 174
array...................................................................................................................................................................186, 188
artificial intelligence ..........................................................................................................................................158, 183
ASW ..........................................................................................................................................................126, 127, 150
ATE ...........................................................................................................................................................................121
attack helicopter.................................................................................................................................................151, 152
Attrition .....................................................................................................................................................................147
Augmentation ............................................................................................................................................................174
Automatic Trainer Test Procedures Guide ................................................................................................................183
Autonomous flight operation & mission control .......................................................................................................128
avionics......................................................................................................................................129, 135, 136, 140, 143
Ballistic Damage........................................................................................................................................................151
Ballistic Tolerance.....................................................................................................................................................151
Beam..................................................................................................................................................................115, 186
bearings .............................................................................................................................................................115, 124
BEM/FEM .................................................................................................................................................................114
BIT.............................................................................................................................................................................137
Broadband .................................................................................................................................................110, 126, 180
C3I .............................................................................................................................................................................158
Canopy Fracturing .....................................................................................................................................................145
Carrier Operations .....................................................................................................................................................146
chaff...........................................................................................................................................................................148
chemical.............................................................................................................................................................110, 175
Chip Architecture ......................................................................................................................................................108
Navy-6
Chips..........................................................................................................................................................108, 113, 149
Chlorofluorocarbon (CFC) ........................................................................................................................................175
Classification .............................................................................................................................................113, 127, 150
Clean Air Act.............................................................................................................................................................175
Close Combat ............................................................................................................................................................129
coating .......................................................................................................................................................125, 139, 141
coatings......................................................................................................................................................125, 134, 139
Cockpit .............................................................................................................................................. 155, 161-164, 166
Cockpit Display .........................................................................................................................................................164
combustion ................................................................................................................................................................178
command and control ................................................................................................................................128, 154, 168
Common Digital Electronic Modules ........................................................................................................................143
communication ..........................................................................................................................................128, 140, 179
communications.........................................................................................................................................140, 167, 180
components........................................................110, 112, 119, 131, 134, 135, 137, 138, 142, 144, 155, 171, 177, 186
composite........................................................................................................... 120, 123, 125, 133-135, 137, 140, 171
composite materials ...................................................................................................................................123, 135, 171
composite structures ..................................................................................................................................................133
composites .........................................................................................120, 123, 125, 133, 135, 136, 138, 140, 141, 171
Computer Chip ..........................................................................................................................................................113
controls ......................................................................................................................................140, 161, 162, 173, 174
Cooling ......................................................................................................................................................................136
Coordination ......................................................................................................................................................110, 158
corrosion....................................................................................................................................................111, 138, 141
Cost Effectiveness .............................................................................................................................................151, 152
countermeasure..........................................................................................................................................................169
crack growth ..............................................................................................................................................................142
Crack Initiation..........................................................................................................................................................142
crashworthiness .........................................................................................................................................................152
crashworthy design....................................................................................................................................................152
Criticality Analysis ....................................................................................................................................................116
CRT Displays ............................................................................................................................................................163
cruise missile .............................................................................................................................................................154
cure cycle...................................................................................................................................................................123
data acquisition..........................................................................................................................................................181
decision-making ........................................................................................................................................................146
Degradable.................................................................................................................................................................148
Degradation ...............................................................................................................................108, 120, 138, 141, 159
Design Influence........................................................................................................................................................146
detectors.....................................................................................................................................................................185
Detonating Cord ........................................................................................................................................................145
DI Simulation ............................................................................................................................................................155
diagnostic...........................................................................................................................................................111, 143
Diesel Engine.............................................................................................................................................................177
Diesel Engines ...................................................................................................................................................176, 178
DIFAR ......................................................................................................................................................................126
digital.................................................................................................................................................137, 143, 159, 183
display ....................................................................................................................................... 117, 162-164, 166, 179
Display Controls........................................................................................................................................................162
displays .............................................................................................................................. 117, 127, 161-164, 166, 179
Distributed Computing ..............................................................................................................................................112
Domain Model...........................................................................................................................................................157
Doppler Shift .............................................................................................................................................................170
Navy-7
ECCM........................................................................................................................................................................172
ECM ..................................................................................................................................................................168, 172
Ecology......................................................................................................................................................................175
Ejection..............................................................................................................................................................144, 145
Ejection Sequencer ....................................................................................................................................................144
Elastic Bodies ............................................................................................................................................................114
electromagnetic..................................................................................................................................................131, 140
Electronic Countermeasures ......................................................................................................................................168
electronic packaging..........................................................................................................................................135, 136
electronic warfare ..............................................................................................................................................168, 180
Embedded ..........................................................................................................................................................107, 140
Enclosures .................................................................................................................................................135, 136, 184
engine ................................................................................................................................................ 124, 125, 176-179
Engine Air Filter........................................................................................................................................................176
engines............................................................................................................................................... 124, 125, 176-179
Environment ...................................... 120, 129, 131, 136, 140, 146, 150, 153, 156, 158, 160, 164, 166, 172, 180-181
environmental degradation ........................................................................................................................................159
Environmental Measurement.....................................................................................................................................109
Environmentally ................................................................................................................................................122, 148
Equipment Design .....................................................................................................................................................179
Escape................................................................................................................................................................139, 145
expert system .............................................................................................................................................................149
Eye Point ...................................................................................................................................................................161
F-14 ...........................................................................................................................................................................115
fabrication.......................................................................................................... 113, 125, 133, 134, 137, 144, 176-178
Failure Detection .......................................................................................................................................................121
Failure Modes Effects................................................................................................................................................116
fatigue........................................................................................................................................................ 123-125, 165
Fault Coverage Metrics .............................................................................................................................................143
ferroelectric................................................................................................................................................................117
Ferroelectric Liquid Crystal Displays .......................................................................................................................117
Fiber...................................................................................................................................117, 120, 125, 148, 167, 171
fiber optic ..................................................................................................................................................................117
fiber optics .................................................................................................................................................................167
Fibers .................................................................................................................................................125, 135, 140, 182
field tests....................................................................................................................................................................132
filtration .....................................................................................................................................................................176
Fire Damage ..............................................................................................................................................................171
Flat Panel Conversion................................................................................................................................................166
Flat Panel Displays .................................................................................................................................... 161-163, 166
Flight .................................... 115, 128-129, 137, 140, 142, 153, 155-158, 161-162, 164-166, 173-174, 178, 181, 183
flight control ..............................................................................................................................................173, 174, 183
Flight Controls...................................................................................................................................................161, 174
Flight Simulation .......................................................................................................................................................157
flight simulator ..........................................................................................................................................................155
Flightcrew..................................................................................................................................................................158
FLIR ..........................................................................................................................................................................160
Forecasting ................................................................................................................................................................147
fuel.............................................................................................................................................................129, 139, 178
Fuel Tank Coatings....................................................................................................................................................139
Fuel Tank Technology...............................................................................................................................................139
fusion .........................................................................................................................................................................153
Navy-8
Fuzzy Logic .......................................................................................................................................................149, 174
Galvanic.....................................................................................................................................................120, 138, 141
gas turbine engines ............................................................................................................................................124, 125
glass ...........................................................................................................................................................................171
GPS............................................................................................................................................................................132
Graphic Image Fusion ...............................................................................................................................................153
graphics .....................................................................................................................................................................153
Graphite .....................................................................................................................................120, 123, 135, 138, 171
Graphite/Epoxy Composites......................................................................................................................................123
grinding .....................................................................................................................................................................118
Halons Destruction ....................................................................................................................................................175
Handling Characteristics............................................................................................................................................164
Heads Up Display......................................................................................................................................................164
heat damage ...............................................................................................................................................................171
Heatsinks ...................................................................................................................................................................135
helicopter ...........................................................................................................................128, 151, 152, 155, 156, 183
Helicopter 3-D Airspeed............................................................................................................................................156
Helicopter Aerodynamic Flow Field .........................................................................................................................156
Helicopter Simulator Cue Requirements ..................................................................................................................155
Helicopter Simulator Fidelity ....................................................................................................................................155
helmet mounted display.............................................................................................................................................166
HERO (Hazards of Electromagnetic Radiation to Ordnance) ...................................................................................131
high performance...............................................................................................................120, 133, 135, 136, 140, 174
high temperature........................................................................................................................................................125
HMD..........................................................................................................................................................................166
HUD ..................................................................................................................................................................160, 164
Human Factors................................................................................................................................................... 161-163
humidity.....................................................................................................................................................................137
Hybrid Microelectronics............................................................................................................................................119
Hydraulic Pump.........................................................................................................................................................121
identification......................................................................................................................111, 119, 125, 160, 170, 172
image compression ....................................................................................................................................................149
image enhancement ...................................................................................................................................108, 127, 149
image processing .......................................................................................................................108, 127, 149, 153, 169
Imaging Systems........................................................................................................................................108, 169, 185
Imide/Graphite Composite ........................................................................................................................................120
impact ........................................................................................................................................108, 123, 126, 127, 138
IMU ...........................................................................................................................................................................132
Inflight Refueling Probe ....................................................................................................................................164, 165
infrared ..............................................................................................................129, 159, 160, 168, 169, 182, 187, 188
installation .................................................................................................................................121, 127, 156, 165, 181
instrumentation .................................................................................................. 109, 110, 156, 161-163, 166, 178, 181
insulation ...................................................................................................................................................................141
Integral Fuel Tank .....................................................................................................................................................139
Intercommunications System.....................................................................................................................................167
interference ................................................................................................................................................................140
interoperability ..........................................................................................................................................................112
IR .......................................................................................................................108, 149, 159, 168, 182, 187, 188, 188
IR Image Processing..................................................................................................................................................149
IR/MMW Measurement ............................................................................................................................................187
ISAR..........................................................................................................................................................................127
Navy-9
JIAWG...............................................................................................................................................................137, 143
JIAWG Diagnostic Initiative .....................................................................................................................................143
joints ..........................................................................................................................................................................111
Laminated Canopy.....................................................................................................................................................145
laser ...........................................................................................................................................................156, 170, 186
Laser Radar (LADAR) ..............................................................................................................................................170
lasers..................................................................................................................................................107, 169, 170, 182
life cycle cost.....................................................................................................................................................146, 167
Life prediction ...........................................................................................................................................................124
Limited Images ..........................................................................................................................................................182
Liquid Penetrant Inspection.......................................................................................................................................122
Load Alleviation........................................................................................................................................................173
Logistics Support Analysis........................................................................................................................................116
low cost......................................................................................................................................109, 110, 118, 180, 186
machine intelligence ..................................................................................................................................................174
Machine Vision .................................................................................................................................................119, 127
machining ..................................................................................................................................................................123
maintainability ...................................................................................................................................................116, 135
maintenance....................................................................................................... 115, 116, 121, 138, 140-142, 146, 187
manufacturing technology ......................................................................................................... 118, 119, 133-135, 140
Map....................................................................................................................................................................137, 154
Maritime ....................................................................................................................................................................129
mass ...........................................................................................................................................................................133
Matched Filtering ......................................................................................................................................................126
materials ............................................................................ 118, 120, 122, 123, 134-136, 139, 141, 151, 171, 177, 186
Matrix Addressable (FLC) Arrays.............................................................................................................................117
Measurement .............................................................................................................109, 110, 119, 123, 143, 178, 187
measurement system..................................................................................................................................................187
metal ..........................................................................................................................................120, 135, 140, 141, 148
metallic ......................................................................................................................................................................142
Millimeter Wave........................................................................................................................................................187
mine ...........................................................................................................................................................................130
Mines .........................................................................................................................................................................130
Missile Domes ...........................................................................................................................................................118
missiles ..............................................................................................................................................................159, 168
Mission Planning ...............................................................................................................................................153, 154
model .........................................................................................117, 128, 132, 146, 149, 155, 157, 159, 173, 174, 184
modeling ....................................................................................................................................................125, 149, 184
Montreal Protocol......................................................................................................................................................175
MOVIESTAR............................................................................................................................................................184
Multi-Sensor Integration ...........................................................................................................................................132
navigation ..................................................................................................................................................................162
Navy trainer Test Procedures Guide..........................................................................................................................183
NDE...........................................................................................................................................................................123
NDE Composites .......................................................................................................................................................123
NDI............................................................................................................................................................................138
neural network ...........................................................................................................................................108, 113, 128
neural networks .........................................................................................................................................................128
Neutron Radiography ................................................................................................................................................185
Ni-alloy Corrosion.....................................................................................................................................................111
Navy-10
noise reduction ..........................................................................................................................................................149
non-acoustic...............................................................................................................................................................127
non-contact measurement ..........................................................................................................................................119
Non-Cooperative ...............................................................................................................................................170, 172
Nonlinear Dynamics ..................................................................................................................................................107
Nonlinear Optical Polymer........................................................................................................................................186
Object Recognition....................................................................................................................................................113
OFT Testing ..............................................................................................................................................................183
Optical ....................................................................................................... 110, 117-119, 137, 140, 169, 170, 182, 186
optical correlator........................................................................................................................................................169
Optical Disk...............................................................................................................................................................137
optical fibers .............................................................................................................................................................182
Optical Fibers Coherent Imaging Diffraction............................................................................................................182
optical processing ......................................................................................................................................................169
Optics.................................................................................................................................................107, 118, 167, 169
optimization...............................................................................................................................................................132
packaging........................................................................................................................................... 135-137, 140, 148
passive ...............................................................................................................................................................126, 187
performance.......................... 120, 122, 126-127, 133, 135-138, 140-141, 155, 165, 171-172, 174, 178, 180-181, 186
periscope....................................................................................................................................................................127
Piezoelectric ..............................................................................................................................................................134
Polishing....................................................................................................................................................................118
Polyamide ..........................................................................................................................................................138, 141
polymer......................................................................................................................................120, 133, 135, 140, 186
Polymer Composite ...................................................................................................................................................120
polymers ....................................................................................................................................................................186
processing..........................................................................108, 120, 124, 126, 127, 134, 136, 140, 149, 153, 169, 172
propulsion.......................................................................................................................................... 124, 125, 175-179
protocol......................................................................................................................................................................175
radar...........................................................................................................................129, 160, 168, 170, 172, 180, 186
RADHAZ ..................................................................................................................................................................131
Radiated Environment ...............................................................................................................................................180
radiation.....................................................................................................................................107, 131, 168, 169, 184
Radiation Hazard Primer ...........................................................................................................................................131
Radiation Heat Transfer ............................................................................................................................................184
radiography................................................................................................................................................................185
Real Time Radiography.............................................................................................................................................185
real-time.....................................................................................................................108, 112, 127, 140, 169, 170, 185
receivers.....................................................................................................................................................................110
Reliability Centered Maintenance .............................................................................................................................116
Reliability Program....................................................................................................................................................116
Residual Stress Measurement ....................................................................................................................................123
Reusability.................................................................................................................................................................157
REWRITABLE .........................................................................................................................................................137
RF ..............................................................................................................................................................169, 180, 188
RF Transmitting Screen.............................................................................................................................................188
Ride Maneuver Control .............................................................................................................................................173
rotorcraft............................................................................................................................................................155, 183
SAR ...........................................................................................................................................................................127
SBIR ..................................................................................................................118, 132, 150, 153, 170, 173, 177, 189
Scavenger .................................................................................................................................................................141
Navy-11
Seawater Pipe Corrosion ...........................................................................................................................................111
seeker.........................................................................................................................................................................149
SEM-E .......................................................................................................................................................................137
semiconductor............................................................................................................................................................131
semiconductor technology.........................................................................................................................................131
sensor.........................................................................................109, 110, 119, 132, 134, 142, 156, 160, 172, 174, 187
Sensor Based Manufacturing.....................................................................................................................................119
Sensor Interpretation .................................................................................................................................................160
Sensor System ...................................................................................................................................................109, 142
sensors ................................................................ 108-110, 113, 115, 119, 126-129, 132, 134, 140, 150, 160, 169, 182
shallow water.............................................................................................................................................................127
Shipboard Landing Simulation..................................................................................................................................155
signal processing ...............................................................................................................................................126, 172
Silicon carbide ...................................................................................................................................................125, 135
simulation .................................................................................................................. 128, 143, 155-157, 159, 173, 174
simulator ............................................................................................................................................121, 155, 180, 188
simulators ..........................................................................................................................................................158, 160
SINDA.......................................................................................................................................................................184
small engine...............................................................................................................................................................177
smart skins .................................................................................................................................................................140
Software...............................................112, 114, 116, 119, 126-127, 137, 139, 154, 157-158, 160, 174, 179, 183-184
Spares .......................................................................................................................................................................147
spatial resolution........................................................................................................................................................185
Stability..............................................................................................................................107, 125, 129, 133, 170, 174
Stabilized Glideslope Displays ..................................................................................................................................117
Statistical Process Control .........................................................................................................................................119
Steering......................................................................................................................................................................186
Stratospheric Ozone Depletion..................................................................................................................................175
structural............................................................................................................ 114, 123, 133, 138, 140-142, 171, 173
Structural Vibration Control......................................................................................................................................173
structures ........................................................................................................................................... 114, 133, 140-142
Subcooled ..................................................................................................................................................................136
submarines.................................................................................................................................................................126
Substrates...................................................................................................................................................................135
supportability.............................................................................................................................................................163
survivability.......................................................................................................................................116, 129, 151, 152
Survival .....................................................................................................................................................................144
System Design ...................................................................................................................................108, 137, 146, 159
System Engineering...................................................................................................................................................116
T&E ...........................................................................................................................................................................180
tactical aircraft ...........................................................................................................................................................133
Tactical Cockpit.........................................................................................................................................................166
Tactical Data......................................................................................................................................................163, 166
Tactical Displays ...............................................................................................................................................161, 162
target..................................................................................................126, 127, 129, 132, 150, 160, 169, 172, 187, 188
target recognition.......................................................................................................................................................169
Target Screen.............................................................................................................................................................188
targeting.....................................................................................................................................................132, 160, 168
Telemetry...................................................................................................................................................................181
TERCOM ..................................................................................................................................................................154
Test ...................................... 111, 115, 119, 122, 124, 135-137, 143, 150, 153, 155-156, 169, 172, 178-183, 185-188
test facilities...............................................................................................................................................................179
test methods ...............................................................................................................................................................181
Navy-12
Thermal...................................................................................... 123, 125, 133, 135-137, 140, 160, 169, 171, 184, 185
Thermal Analyzer ......................................................................................................................................................184
Thermal Damage .......................................................................................................................................................171
Thermal Imagery .......................................................................................................................................................160
Thrust.........................................................................................................................................................................144
thrust vector control...................................................................................................................................................144
titanium......................................................................................................................................................................125
TMG ..........................................................................................................................................................................184
Tooling Concepts.......................................................................................................................................................133
Tooling Improvement ................................................................................................................................................133
toxic ...........................................................................................................................................................................175
tracking..............................................................................................................................................................159, 170
trainers .......................................................................................................................................................................159
training............................................................................................................................................... 153, 155, 157-160
trajectory control .......................................................................................................................................................174
transducer ..........................................................................................................................................................134, 181
transducers.........................................................................................................................................................134, 181
transport.....................................................................................................................................................................137
turbine engine ............................................................................................................................................................124
UAV .......................................................................................................................................... 128, 129, 168, 176-178
unmanned aerial vehicle ............................................................................................................................................129
V-22...........................................................................................................................................................................155
validation ...................................................................................................................................................124, 174, 179
Vector Control ...........................................................................................................................................................144
vehicles .............................................................................................................................. 109, 110, 128, 168, 176-178
verification................................................................................................................................................. 143, 176-178
VHSIC .......................................................................................................................................................................143
video ..........................................................................................................................................108, 153, 159, 169, 187
Virtual................................................................................................................................................................158, 164
vision .........................................................................................................................................113, 119, 127, 145, 160
VLSI ..........................................................................................................................................................................108
VTOL ........................................................................................................................................................................129
vulnerability...............................................................................................................................................................151
VX .............................................................................................................................................................................160
warfare....................................................................................................................... 127, 149, 153, 158, 167-169, 180
Waste .........................................................................................................................................................................122
water ..................................................................................................................................110, 120, 122, 127, 139, 160
Water-borne...............................................................................................................................................................122
waveguide..................................................................................................................................................................186
Wing Fold..................................................................................................................................................................115
WST Testing..............................................................................................................................................................183
Navy-13
DEPARTMENT OF THE NAVY
INDEX OF NAVY TOPICS
OFFICE OF NAVAL RESEARCH
N92-107 TITLE: Nonlinear Dynamical Control of Lasers
N92-108 TITLE: Real Time Image Enhancement
N92-109 TITLE: Platforms for 4-Dimesional Environmental Sensing
N92-110 TITLE: 4-Dimensional Oceanographic Instrumentation
N92-111 TITLE: Remote Sensing of Crevice Corrosion
N92-112 TITLE: Module Interconnection Framework for Software Producibility
N92-113 TITLE: Object Recognition Chip (ORC)
N92-114 TITLE: Improved Methods for Predicting Acoustic Scattering from Submerged Elastic Bodies
NAVAL AIR SYSTEMS COMMAND
N92-115 TITLE: On Aircraft Analysis of F-14 Aircraft Wing Bearings
N92-116 TITLE: Failure Mode Effects and Criticality Analysis Integration Project
N92-117 TITLE: Matrix-Addressable Liquid Crystal Displays for Visual Landing Aids
N92-118 TITLE: Finishing of Optical Domes
N92-119 TITLE: High-Resolution Dimensional-Control-Sensors for Microelectronics Manufacturing
Process
N92-120 TITLE: Imide/Graphite Composite Degradation Characterization
N92-121 TITLE: Aircraft Hydraulic Pump Condition Monitoring System
N92-122 TITLE: Penetrant Materials for Nondestructive Inspection
N92-123 TITLE: Residual Stress Measurement on Graphite/Epoxy Composites
N92-124 TITLE: Establishment of a New Rolling Contact Bearing Life Calculation Method
N92-125 TITLE: Fiber/Matrix Interphases for Silicon Carbide Fiber Reinforced Titanium Matrix
Composites
N92-126 TITLE: Automatic Broadband Matched Filtering
N92-127 TITLE: SAR/ISAR Real Time Image Processing for Air ASW Platforms
N92-128 TITLE: Using Neural Networks for autonomous UAV flight operation and mission control
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N92-129 TITLE: Vertical Takeoff and Landing Unmanned Aerial Vehicle for Maritime and Close Combat
Applications
N92-130 TITLE: Improved Air-Developed Mines
N92-131 TITLE: 20MM Radiation Hazard(RADHAZ) Primer
N92-132 TITLE: Multi-Sensor Integration for High Altitude Bombing
N92-133 TITLE: Tooling Concept for the Fabrication of Large, Complex Composite Structures
N92-134 TITLE: In Situ Process Monitors for Composite Processing
N92-135 TITLE: Composite Material Electronic Enclosures and Circuit Module Heat Sinks/Substrates
N92-136 TITLE: Subcooled Liquid Change of Phase Thermal Management for Electronic Packaging
N92-137 TITLE: Military-Grade 3-1/2 inch Rewritable Optical Disk Drive
N92-138 TITLE: NDI Technique for Galvanic Degradation of Composites
N92-139 TITLE: Application Equipment/Software for Multi-Layer Fuel Tank Coatings
N92-140 TITLE: Composite Embedded Optical Fibers for Communication Links
N92-141 TITLE: Formulation of Effective Corrosion Scavengers
N92-142 TITLE: Localized Sensor System for Damaged Metallic Aircraft Structure
N92-144 TITLE: Improved Capability Electronic Ejection Sequencer (ICEES)
N92-145 TITLE: Innovative Design for Aircraft Canopy Fracturing System
N92-146 TITLE: Life Cycle Cost (LCC) Oriented for Naval Aircraft
N92-147 TITLE Spares Forecasting
N92-148 TITLE: Environmentally Degradable Chaff Packaging
N92-149 TITLE: Infra-red Image Processing Using Fuzzy Logic Expert System Technology
N92-150 TITLE: Air ASW Acoustic Classification
N92-151 TITLE: AH-1W Improved Ballistic Tolerance
N92-152 TITLE: AH-1W Improved Crashworthiness
N92-153 TITLE: Visualization and Analysis for Cruise Missile
N92-154 TITLE: Terrain Contour Matching (TERCOM) Map Placement
N92-155 TITLE: Minimum Simulation Cues Required for the Rotorcraft Shipboard Landing Task
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N92-156 TITLE: Flight Test Instrumentation to Measure the Aerodynamic Flow Field of an H-60
Helicopter
N92-158 TITLE: "Virtual" Air Intercept Control (AIC) Architecture for Training Air Intercept Control
Procedures
N92-159 TITLE: Environmental Degradation Model for Infrared Acquisition and Tracking
N92-160 TITLE: FLIR Training System
N92-161 TITLE: Determination of Actual Eye-point in the E-2C Cockpit
N92-162 TITLE: Determination of cockpit tactical display controls
N92-163 TITLE: Flat panel display technology for the E-2C Cockpit
N92-164 TITLE: Use of Heads Up Displays in the E-2C Cockpit
N92-165 TITLE: Long Duration Missions on the E-2C Aircraft
N92-166 TITLE: Use of Helmet Mounted Displays on the E-2C
N92-167 TITLE: Engineering Economy Analysis of an Intercommunication System Conversion for the E-
2C
N92-168 TITLE: ECM Payloads for UAVs
N92-169 TITLE: Target Aim Point Selection Based on Real Time Optical Processing Visual or Infrared
Generated Scenes
NAVAL AIR DEVELOPMENT CENTER
N92-170 TITLE: LADAR Identification (ID) Demonstration
N92-171 TITLE: Detection of Thermal Damage in Composite Materials
N92-172 TITLE: Aircraft Target Identification in an ECM Environment
N92-173 TITLE: Active Control of Fighter Maneuvers
N92-174 TITLE: Fuzzy Logic Applications to Flight Control
NAVAL AIR ENGINEERING CENTER
N92-175 TITLE: Disposal of Chlorofluorocarbon (CFC) Substances
NAVAL AIR PROPULSION CENTER
N92-176 TITLE: Innovative, Lightweight, And Sample Air Filtration Concepts For Small Displacement
Diesel Engines
N92-177 TITLE: Innovative Unconventional Small Engine Concepts
N92-178 TITLE: Innovative Concepts for Directly Measuring Airflow In Intermittent Combustion Engines
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N92-179 TITLE: Engine control via a standard 1553 bus controller for use at engine test facilities
NAVAL AIR TEST CENTER
N92-180 TITLE: Anechoic Chamber Radiated Environment
N92-181 TITLE: Wireless Airborne Instrumentation System
N93-182 TITLE: Infrared Optical Fibers
N92-183 TITLE: Artificial Intelligence (AI) Technology to Enhance Flight Test Software Configuration
Control
NAVAL WEAPONS CENTER
N92-184 TITLE: Radiation Heat Transfer Analysis
N92-185 TITLE: Improved Thermal Neutron Imaging Method
N92-186 TITLE: Laser Beam Steering Via the Pockels Effect
PACIFIC MISSILE TEST CENTER
N92-187 TITLE: Dual Mode Infrared (IR)/Millimeter Wave (MMW) Measurement System
N92-188 TITLE: Multi-Spectral Scene Generation for Hardware-in-the-loop (HWIL) Laboratories
Navy-17
DEPARTMENT OF THE NAVY
FY 1992 TOPIC DESCRIPTIONS
OFFICE OF NAVAL RESEARCH
N92-107 TITLE: Nonlinear Dynamical Control of Lasers
CATEGORY: Basic Research
OBJECTIVE: To obtain long term stability for the output of lasers via control techniques recently developed in the
field of nonlinear dynamics.
DESCRIPTION: The physics of lasers, and solid state devices and their combination, naturally involves nonlinear
dynamics. Instabilities, chaos, and spatio-temporal pattern formation and competition are common phenomena in
regimes of nonlinear optics. Concomitantly, with an increased interest in the nonlinear dynamics of lasers there has
arisen novel ideas for control of nonlinear systems. For example, these ideas involve stabilizing periodic orbits
embedded in chaotic dynamics. Without control these periodic orbits are unstable.
Phase I: Demonstrate the utility of control techniques developed in nonlinear dynamics for stabilizing lasers,
especially for the generation of blue-green radiation via second harmonic generation from solid state lasers.
Phase II: Apply the techniques developed in Phase I to lasers to achieve long term stability for operational
applications.
N92-108 TITLE: Real Time Image Enhancement
CATEGORY: Basic Research
OBJECTIVE: To develop real-time systems, including VLSI chips, to solve the problems of noise removal, edge
enhancement, dynamic range adjustment, uniformity correction, and color constancy in image sensors and systems.
DESCRIPTION: The problems of noise removal, edge enhancement, dynamic range adjustment, uniformity
correction, and color constancy in imaging systems are extremely computation intensive tasks. These tasks cannot
be done at the needed frame rate even with today's supercomputers. Recently there have been significant advances
in using nearest neighbor interconnect type of architecture to solve the problems of real-time image processing. The
silicon retina and color constancy work at Caltech, and the Cellular Neural Network work at the University of
California readily come to mind.
Research at numerous other universities, such as MIT Lincoln Laboratory and Johns Hopkins University can
also be cited. It has been shown that these locally interconnected architectures, when realized on silicon, can
perform real-time image processing with no degradation on the frame rate. Some small scale research prototype
chips have been designed, and have demonstrated the potentials of the algorithm and architecture. There is no
reason why full-scale system cannot be built to achieve real-time image enhancement. This would have significant
impact on improving the image quality of civilian video, as well as military IR, systems.
Phase I: Identify the research issues associated with developing full-scale VLSI chip or chips to achieve the
stated objective, and to produce the conceptual design of a real-time image enhancement system.
Phase II: Complete the detailed VLSI chip and system design, fabricate the system, and demonstrate the
system to achieve the stated objective in real time.
N92-109 TITLE: Platforms for 4-Dimesional Environmental Sensing
CATEGORY: Basic Research
OBJECTIVE: To adapt available airborne/underwater remote operated vehicles to sensors for measuring 4-
dimensional environmental parameters.
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DESCRIPTION: Both Autonomous Underwater Vehicles (AUVs) and Remotely Operated Vehicles (ROVs) have
been developed and used for specific applications such as location of opposition emplacements during Desert
Storm. The increased emphasis on global climate change and the difficulty and expense in acquiring affordable 4-
dimensional environmental sensing data strongly suggest application of low cost remotely operated vehicles for
environmental parameter measurement. A vehicle/sensor system integration analysis is desired to identify the
compatible measurements that are possible, the state of the art instrumentation required, the payload requirements
versus mission, the power requirements and endurance, and the vehicle and control system description.
Phase I: A description of the sensor/platform system, what would be measured, and why a remotely controlled
platform is scientifically/fiscally superior to the present methods of making such measurements would be
documented. Phase I should produce a report that identifies concepts that could be tested in Phase II.
Phase II: Build the system identified in Phase I and demonstrate its predicted capabilities.
N92-110 TITLE: 4-Dimensional Oceanographic Instrumentation
CATEGORY: Basic Research
OBJECTIVE: To develop innovative instrumentation to measure oceanographic/meteorologic parameters.
DESCRIPTION: Innovative sensors/projectors and measurement techniques are solicited to obtain marine
atmospheric, oceanographic (acoustical, optical, physical, biological, chemical, and geophysical) variables in 3D
space and time. The emphasis is on (1) novel approaches and concepts for measuring multiple parameters
coherently in 4D; (2) new methods of measuring fluxes, acoustic wavefields, or fluid motion of mixtures (i.e.
water/bubbles/sediments/biologics). Instruments can be towed/tethered sensors/projectors, elements in arrays, or
suites of instruments on ROVs(remotely operated vehicles) to cite a few examples. Low cost, reliable, and/or
expendable sensors/projectors and components (e.g. broadband, large dynamic range, high efficiency, compact, low
power consumption projector/receivers) are particularly desirable. Full depth capability is desired in instrumentation
planned for subsurface use.
Phase I: Provide a description of exactly what will be measured and to what accuracies and coherence as well
as providing the design concept for achieving the measurements. Phase I should produce a proof of concept by
demonstrating untested concepts or instruments.
Phase II: Develop hardware and demonstrate feasibility in the laboratory. Field testing should be addressed
via coordination with ongoing ONR field efforts. Potential approaches to industrial development that transition
program output should also be outlined.
N92-111 TITLE: Remote Sensing of Crevice Corrosion
CATEGORY: Basic Research
OBJECTIVE: To develop a remote sensing technique to detect crevice corrosion.
DESCRIPTION: Crevice corrosion is a form of localized corrosion that can occur within crevices or at shielded
surfaces where a stagnant solution is present. Crevices formed by the contacting surfaces of a gasket and a flange
face in the presence of seawater have been particularly troublesome for the Navy in assembled seawater pipe
networks where numerous gasketed junctions exist. The disassembling of pipe joints comprising gasketed flanges
for crevice corrosion examination is tedious, difficult, and expensive. The ability to determine, without
disassembling and inspection, whether crevice corrosion is occurring, or has occurred, within an assembled
gasketed flange joint would be of great benefit to Navy operations.
Phase I: Address remote sensing concepts for crevice corrosion which are capable of being developed into
rapid diagnostic procedures.
Phase II: The identified Phase I concept will be further developed and verified in simulated service situations
using gasketed Ni-Cr-Mo-Fe alloys, such as Alloy 625, and chlorinated seawater, and a diagnostic procedure for the
remote identification of crevice corrosion will be made available. The diagnostic procedure may comprise portable
equipment, a test kit, or a service.
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N92-112 TITLE: Module Interconnection Framework for Software Producibility
CATEGORY: Basic Research
OBJECTIVE: To develop a module interconnection framework for distributed applications programming.
DESCRIPTION: The great diversity of computing systems and software has created a major problem in the
interoperability and integration of heterogenous systems and components. Recent research is exploring the
technologies of open-system architectures, type theories, parameterized programming, real-time/fault-tolerant
(RT/FT) systems theory, interconnection technologies, and module interconnection frameworks (MIF). These
technologies facilitate the interconnection of systems and software components written in diverse source languages
on networked architectures. Software producibility, usability and system evolution will be greatly improved
through this important technology.
Phase I: The objective is to design a MIF system for the development of software for distributed computing.
The design should describe the mathematical semantics of the MIF, its capability to seamlessly compose software
modules, its capability to handle abnormal events, its capability to manage RT/FT events, and its capability to
analyze properties of systems built from MIFs. The use of the MIF should be illustrated through the development of
the basic features of a distributed spread-sheet application.
Phase II: An experimental research prototype based on the Phase I MIF design will be developed.
N92-113 TITLE: Object Recognition Chip (ORC)
CATEGORY: Basic Research
OBJECTIVE: Recent advances in multi-layer networks and "retina-like" silicon devices have made possible a new
generation of sensors - i.e. chips that can recognize and/or classify objects. So-called "neural-network hybrid"
systems may provide a method to accomplish this goal. At the minimum, an ORC should include "retinal" layers;
a layer or circuit to deal with changes in the shape, scale, and rotation of the visual field; and a "classifier" circuit.
The chip should work in real time and be programmable for different objects. Devices that propose to incorporate
algorithms derived from biological systems (e.g. vision, pattern classification) are of special interest.
Phase I: Address issues and concepts so as to demonstrate the feasibility of such a chip. This might include
presenting a detailed architecture, specifications, and a schedule for prototype production.
Phase II: Include design completion, fabrication, testing and debugging to produce a fully functional
prototype.
N92-114 TITLE: Improved Methods for Predicting Acoustic Scattering from Submerged Elastic Bodies
CATEGORY: Basic Research
OBJECTIVE: To develop methods to overcome certain difficulties in applying boundary element/finite element
methods to acoustic scattering from elastic bodies.
DESCRIPTION: The Navy has an interest in predicting acoustic scattering from submerged elastic bodies.
Anticipated advances in computer capabilities will allow current structural-acoustic boundary element method-finite
element method (BEM/FEM) techniques to be implemented at higher and higher frequencies. However, issues that
are not necessarily solved by such advances and may limit prediction capability include the influences of damping,
complex internal structures, appendages with small thickness-to acoustic wavelength ratios, and parameter
uncertainties. ONR is interested in innovative approaches to some or all of the above issues that affect BEM/FEM
structural acoustics predictions.
Phase I: Demonstrate the criticality of a particular issue or set of issues and demonstrate the potential of a
method or methods to address the issue or issues.
Phase II: Produce software implementing the method or methods from above into a full 3-D or semi-3-D
BEM/FEM code.
Navy-20
NAVAL AIR SYSTEMS COMMAND
N92-115 TITLE: On Aircraft Analysis of F-14 Aircraft Wing Bearings
CATEGORY: Engineering Development
OBJECTIVE: To develop a test procedure which will identify faulty wing pivot bearings without removing the
wing assemblies from the aircraft.
DESCRIPTION: This "on the aircraft" test will enable detection of faulty wing bearings as problems occur. The
present method of replacing bearings on a set time schedule is not effective. Faulty bearings are not detected when
they fail and many good bearings are replaced unnecessarily. Currently there is no way to test the wing pivot
bearings without removing wings from the aircraft. When wing sweep causes excessive bearing noise, aircraft are
routed to DEPOT for maintenance. In addition to the excessive maintenance cost of replacing good bearings, faulty
bearings on operating aircraft could bind causing the race in the wing or box beam to rotate. Under dynamic flight
conditions this could cause cracks in the box beam and result in safety-of-flight problems.
Aircraft wing pivot bearings will be tested using the aircraft wing sweep functions as a low speed
dynamometer. Either force detection sensors or tensiometer readouts could be used to measure the frictional forces
as the wings are swept. Specifications for friction tolerances will be developed by empirical analysis on several F-
14 aircraft or through theoretical analysis of aircraft loads. The Government will provide access to F-14 aircraft and
the necessary ground support equipment to test the wing bearings.
Phase I: Studies and experiments shall be performed to determine the feasibility of developing a
comprehensive "on the aircraft" test of wing pivot bearing. Phase I shall provide a report which will include the
analysis and relevant data to support the findings.
Phase II: The objectives of this phase are to develop specifications for wing bearing friction and to develop
the process and procedures for "on the aircraft" testing of wing pivot bearings. Prototype of ground support
equipment required to perform the test will be developed during this phase.
N92-116 TITLE: Failure Mode Effects and Criticality Analysis Integration Project
CATEGORY: Engineering Development
OBJECTIVE: The project will create a tool to link the reliability program Failure Modes, Effects and Criticality
Analysis (FMECA) to the logistics and related programs. The project will (1) develop a standard methodology for
the analysis, and (2) develop software to automate and document the analysis. Benefits from standardizing and
automating the analysis will be (1) standard definitions and processes, (2) earlier development of the data, (3) fewer
person-hours required for the analysis, and (4) a common data base between the reliability and logistics programs.
DESCRIPTION: In Phase I, a step by step FMECA methodology for both a top down and bottom up approach
shall be developed to provide a standard process for the analysis. Definitions and data requirements for the
following programs shall be incorporated in the methodology: (1) Reliability & Maintainability, (2) Logistic
Support Analysis, (3) System Safety, (4) Reliability Centered Maintenance (RCM), and (5) Survivability. In Phase
2, the contractor shall develop software that utilizes the methodology to perform and document a FMECA. The
software shall be developed for an IBM personal computer and Vax computer. The software shall provide a process
for performing a top down FMECA to the 5 digit work unit code and a bottom up FMECA starting at a piece part
level and going up to the WRA/subsystem/system indenture level. The software will operate as a stand alone,
relational data base, requiring no other software for operation. The software will be menu driven. All commands
will be displayed on the screen. Help screens will be provided to explain software operation, data element
definitions, data entry, and report generation.
N92-117 TITLE: Matrix-Addressable Liquid Crystal Displays for Visual Landing Aids
CATEGORY: Engineering Development
Navy-21
OBJECTIVE: To develop stabilized optical landing aids with no moving parts by implementing matrix addressable
Ferroelectric Liquid Crystal (FLC) displays to produce a slot that will form the object for an optical system. If
successful, this concept will eliminate mechanical/electrical drive systems on shipboard stabilized systems with
fixed azimuth display angles (i.e., FLOLS and VSTOL OLS).
DESCRIPTION: The matrix liquid crystal display will be computer driven. The object, a rectangular slot .05 by 4
inches, formed by the display matrix must be capable of transmitting visible light. The matrix display will be placed
between a light source and an optical lens system to produce a stabilized light bar that is projected into space to
provide pilots a glideslope display. The matrix crystal display must be able to shift the slot (object) vertically +/- 2
inches, as well as rotate it +/- 25 degrees. Pixel spacing center-to-center must be less than .01 inches. A maximum
frame rate of 90 Hz is required. Ship motion would be compensated for by changing the position of a light bar on a
liquid crystal display matrix. The display matrix would be positioned behind a lens and would replace the moving
fiber optic block concept now used in the VSTOL Program.
Phase I: Should produce a final report outlining the approach undertaken to pursue the requirements above
with sufficient data to demonstrate the feasibility of the concept.
Phase II: Should use the approach outlined in Phase I to produce a working model that demonstrates the
concepts outlined above and can be field tested at NAEC.
N92-118 TITLE: Finishing of Optical Domes
CATEGORY: Exploratory Development
OBJECTIVE: The objective of this work is to investigate the finishing processes used and to establish low cost
techniques to obtain the required final product.
DESCRIPTION: The processes used are scooping, grinding, and polishing. The curvature, thickness, and surface
finish are extremely critical to the utility of the domes. Sapphire is the primary application for this finishing
process, however, the techniques developed would be applicable to all domes regardless of the basic materials used.
These processes need to be defined in detail and their feasibility demonstrated.
Certain cost drivers in the manufacturing of optical domes for missile systems have been addressed through
SBIR and other programs. One area that has not been addressed is the finishing processes used to provide for the
final configuration of domes. The costs of these processes remain high. Presently these costs can be more than
50% of the total cost of a dome.
Phase I: Develop and provide a proposed Phase II program plan to develop a working prototype system to
finish sapphire domes.
Phase II: Develop and demonstrate a prototype system to finish sapphire domes and provide a specified
number of finished domes.
N92-119 TITLE: High-Resolution Dimensional-Control-Sensors for Microelectronics Manufacturing Process
CATEGORY: Exploratory Development
OBJECTIVE: To develop high resolution sensors for dimensional measurement of microelectronic circuits and
components. Measurement data can be used in closed-loop process control algorithms for guidance, alignment, and
inspection. Successful achievement of this project will create a high speed, high resolution, non-contact
measurement (monitoring) technique (system), which assures quality consistencies among weapon systems, and
eliminates tedious manual inspection and repair efforts.
DESCRIPTION: Production yield and hardware reliability is heavily dependent on the dimensional and positional
feedbacks throughout the manufacturing process. At present, the lack of high resolution, non-contact sensors
dictates that check points have to be placed at different stages of the manufacturing cycle and processes, so that
actual condition of the hardware being produced, can be monitored and fed back for process control.
Phase I: Requires research and identification of relevant sensor technologies, its interface schemes and
specifications of the system including hardware, software and procedures.
Navy-22
Phase II: Requires production of a fully documented prototype system and demonstration test with samples
supplied by the Navy.
N92-120 TITLE: Imide/Graphite Composite Degradation Characterization
CATEGORY: Engineering Development
OBJECTIVE: To establish the mechanism of degradation at the molecular level of imide-based graphite composites
when in electrical contact with a corroding metal in an electrolytic salt water solution. The degradation
determination will focus on the fiber/resin interface chemistry, resin chemistry and other potential areas which
affect the mechanism. Once the mechanism is established, modifications to current imide resins as well as
recommendations on new resin development shall be investigated.
DESCRIPTION: Imide-based polymer composites provided elevated temperature performance beyond the current
epoxy systems. The use of these systems can substantially reduce aircraft weight and improve performance. The
purpose of this program is to provide a technical foundation for high performance bismaleimide graphite composites
which do not degrade when exposed to a galvanic couple with a corroding metal in salt water representative of the
Navy environment.
Phase I: Shall conduct a thorough investigation of the phenomena as it is understood and evaluate at the
molecular level the degradation mechanisms and the potential methods for blocking the reaction through polymer
modifications and synthesis.
Phase II: Shall develop at the laboratory level modified bismaleimide resins and composites and/or conduct
synthesis studies on new resin approaches to meet the requirement for elevated temperature composites with greater
than 250F. Tests shall be conducted to demonstrate processing and mechanical properties as well as compare to
baseline materials
N92-121 TITLE: Aircraft Hydraulic Pump Condition Monitoring System
CATEGORY: Advanced Development
OBJECTIVE: To develop a device (other than flow and temperature measuring device) that continuously monitors
the condition of the pump and detects impending failures. If successful, this device will greatly reduce maintenance
man hours and aircraft down time, by removing the pumps before they fail catastrophically.
DESCRIPTION: Currently, the majority of hydraulic pumps are removed from the aircraft only upon failure. A
pump that fails catastrophically generates debris to contaminate the system and it compromises aircraft and aircrew
safety. The existing detection methods of temperature and flow provide data regarding the flow variation with
systems condition but they do not preclude a catastrophic pump failure. Viable methods to identify imminent
monitoring.
Phase I: Develop and propose an approach to show feasibility of meeting requirements.
Phase II: Use Phase I results and verify feasibility by providing prototypes for installation and testing on a
ground simulator.
N92-122 TITLE: Penetrant Materials for Nondestructive Inspection
CATEGORY: Advanced Development
OBJECTIVE: Develop new liquid penetrant (PT) inspection materials formulations that will meet the performance
requirements of specifications MIL-I-25135 and MIL-STD-6866 using water-borne technologies.
DESCRIPTION: Due to environmental restrictions, PT waste must be processed though a licensed disposal
company or retreatment to reduce the total organic content and to remove the fluorence. The rinse water used to
wash the penetrant from the test surface (effluent), spent materials and tank deterioration products are among the
Navy-23
types of penetrant waste. Innovative research is needed to produce more environmentally acceptable PT materials
in which organically based solvents, carriers and developers are replaced by water-borne materials.
Phase I: Identify and demonstrate the feasibility of new formulation(s) of PT materials. Preliminary testing
shall be conducted to demonstrate the feasibility of application and performance of the materials in addition to
preliminary screening to demonstrate that the materials are non-corrosive.
Phase II: Candidate PT materials shall be developed and thoroughly evaluated by the contractor. In addition,
batch samples of the materials shall be supplied to the Navy for evaluation at a field activity. The primary goal shall
be to qualify the PT materials to MIL-I-25135.
N92-123 TITLE: Residual Stress Measurement on Graphite/Epoxy Composites
CATEGORY: Engineering Development
OBJECTIVE: To develop nondestructive methods and analytical techniques to determine the residual stresses in
advanced composite materials. Residual stresses of high strain aircraft structure developed during the cure process
can adversely impact the static and fatigue properties of representative laminates. Post cure stresses from
machining, drilling, thermal cycles, loads etc. can cause laminates to crack unpredictably. These stresses must be
fully understood and accounted for in the design/manufacturing process.
DESCRIPTION: The development of residual stress measurement techniques is essential to ensuring the structural
integrity of high strain aircraft structure. The contractor should address state-of-the-art Navy aircraft composite
systems, laminate stacking techniques, cure cycle variations, thickness and externally induced loads such as drilling,
machining, thermal cycling and structural. The contractor shall address sensitivities in laminate stacking sequence,
cure cycle variation, tooling materials and the detectability of residual stresses.
Phase I: Should consist of a study outlining the methodology to address the above issues with sufficient data
to demonstrate feasibility.
Phase II: Should use the approach outlined in Phase 1 to develop and demonstrate techniques to measure
residual stresses in graphite/epoxy composite representative of those in use in Navy aircraft.
N92-124 TITLE: Establishment of a New Rolling Contact Bearing Life Calculation Method
CATEGORY: Exploratory Development
OBJECTIVE: Establish, validate, and standardize a new rolling contact bearing life calculation method for use in
the design of new gas turbine engine and power drive system bearings.
DESCRIPTION: Aeronautical rolling element bearings are designed, primarily, to meet life requirements as
dictated by the endurance considerations of gas turbine engine and power drive systems. Currently, the Lundberg-
Palmgren theory is utilized as a basis for life prediction, but this theory is, to a large extent, dependant on empirical
material and lubrication factors. Inconsistencies between predicted and actual bearing lives, owed to advances in
material processing and more precise manufacturing techniques, have transformed the present method into an
overly conservative design tool, thereby placing unrealistic size requirements on bearing designed for the next
generation propulsion systems. A number of new life prediction theories, introducing the concept that an inherent
endurance limit exists in bearings, have been developed recently, but presently remain unvalidated. The goal of this
effort is to establish a new standardized rolling contact bearing life calculation method by validating one of the
recently developed theories. Tri-Service acceptance of the new method will be required eventually.
Phase I: The investigations should include a survey of current bearing life analysis methods and prediction
and an initial definition and preliminary validation of the proposed advanced technique. Proposed validation
techniques should include utilization of existing life data as much as possible.
Phase II: The method selected as part of the Phase I effort should be comprehensively validated. This may be
accomplished by utilizing existing life data and through the development of an element test plan for the purpose of
assigning values to each of the primary factors which affect bearing life and testing as required for specific
validation. A comprehensive methodology for life analysis based on the new technique will be presented at the
conclusion Phase II.
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N92-125 TITLE: Fiber/Matrix Interphases for Silicon Carbide Fiber Reinforced Titanium Matrix Composites
CATEGORY: Exploratory Development
OBJECTIVE: To develop a fiber coating system for silicon carbide fibers which is thermally, chemically and
mechanically compatible with advanced titanium alloy matrices.
DESCRIPTION: Silicon carbide (SiC) fiber reinforced titanium matrix composites are an attractive replacement
material for superalloys in future aircraft gas turbine engines. A fundamental problem with these composites is the
reaction zone that grows at the fiber/matrix interface during fabrication and high temperature excursions. The
reaction zone properties are sufficiently different from those of the fiber and matrix, that damaging residual stresses
can be generated. Carbon coatings have been used to relieve some of the stresses and have resulted in acceptable
composite static strengths. However, during high temperature exposure, the carbon interphase reacts with the
matrix to form titanium carbides and other reaction products and causes the thermal/mechanical fatigue behavior of
these composites to be relatively poor. This problem may be addressed by investigating alternative barrier coatings
at the fiber/matrix interface to not only reduce the residual stresses but also prevent the growth of reaction products.
Phase I: The investigations should include the identification of potentially appropriate interphases,
thermodynamic modeling to estimate the growth of reaction products, micromechanical modeling to estimate
residual stress states, as well as fabrication and testing of selected composites. The expected deliverable from this
contract is a final report with sufficient data to demonstrate feasibility.
Phase II: The interphase approach demonstrated under Phase I would be validated by fabricating and testing
an engine part, emphasizing thermal and mechanical fatigue enhancement as well as stability.
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N92-126 TITLE: Automatic Broadband Matched Filtering
CATEGORY: Exploratory Development
OBJECTIVE: Identify, implement, and demonstrate automatic, dynamic matched filtering algorithms for use in
broadband acoustic signal processing, for air ASW applications. If successful, these algorithms will be installed in
fleet special purpose processing systems.
DESCRIPTION: The continually evolving threat, including quieter submarines and the reemergence of third world
diesels, is negatively affecting the detection performance of narrowband acoustic signals. Broadband processing has
become a more important player in passive acoustic detection. Target broadband characteristics, including
bandwidth, may change dynamically in real time. This effort will survey and identify broadband processing
algorithms for DIFAR sonobuoys, investigate them, implement selected processing in a breadboard configuration,
and demonstrate it. The demonstration hardware must be compatible with and interfaced to a VME bus. These
algorithms will automatically sample different frequency bandwidths, monitor, and track their characteristics. They
will provide a dynamic matched filtering capability, which will automatically adjust the processing frequency
bandwidth for each band. The DIFAR broadband data also will be processed and sorted by bearing. The end result
will optimize the signal-to-noise ratio for each broadband band being processed, in real time.
Phase I: Survey existing and proposed broadband algorithms, analyze them, and identify those with the
greatest potential for use in DIFAR broadband matched filter processing in Navy ASW aircraft. The impact of
dynamic matched filter processing on existing Air ASW broadband signal processing will be determined. The
deliverable will be a final technical report fully documenting the work.
Phase II: The processing identified in Phase I will be investigated, implemented on a VME bus compatible
board, and demonstrated using GFI DIFAR data tapes. Deliverables will be a final technical report, a demonstration,
and the documented breadboard hardware/software package.
N92-127 TITLE: SAR/ISAR Real Time Image Processing for Air ASW Platforms
CATEGORY: Exploratory Development
OBJECTIVE: Identify, implement and investigate state-of-the-art mathematical processing techniques for reducing
clutter and for enhancing target images on SAR/ISAR displays. If successful, this processing would be incorporated
in SAR/ISAR systems being considered for installation on Navy Anti-Submarine Warfare (ASW) aircraft.
DESCRIPTION: As targets become acoustically quieter, and as shallow water, LIC and Third World scenarios
emerge in importance, Navy Air ASW must adopt optimum non-acoustic techniques to counter new threats in new
situations. Use of SAR/ISAR for periscope and other small signature target automatic detection is one option under
consideration. Enhancement of SAR/ISAR system detectability may be a deciding factor in determining the
feasibility of using these systems. Numerous mathematical approaches exist, and have been applied in other
contexts, which promise such a detectability increase by reducing sea surface noise clutter/speckle or by enhancing
target signatures. A few examples are image processing, Machine Vision technology, and chaos/fractal processing.
These and other methodologies will be identified, implemented in the laboratory, and investigated for impact on
detection performance. A variety of existing SAR/ISAR systems, operation modes, and parameter combinations will
be considered in this analysis. Realistic synthetic targets superposed on real clutter, or real data tapes provided by
the Navy may be used.
The effort will identify and select those techniques which have the most potential for use in Navy P-3C ASW
missions, and demonstrate them. Emphasis will be on detection and classification of small signature targets such as
periscopes, etc.
Phase I: Survey available methodologies for clutter reduction and for target enhancement, and identify those
with the greatest potential for use on Navy ASW aircraft. The deliverable will be a final technical report fully
documenting the Phase I work.
Phase II: The technologies identified in Phase I will be implemented and demonstrated using synthetic data
and GFI SAR/ISAR data tapes. Detection performance will be investigated.
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Deliverables will be a final technical report, a demonstration, and a documented software package incorporating the
selected technology.
N92-128 TITLE: Using Neural Networks for autonomous UAV flight operation and mission control
CATEGORY: Exploratory Development
OBJECTIVE: Develop a simulation model and demonstrate the advantages of using the neural networks
applications for autonomous multiple UAV operations.
DESCRIPTION: Neural networks have been pursued by some researchers as particularly adept at control functions
for systems that are nonlinear and which are not well characterized mathematically. A variety of neural networks
approaches have demonstrated the ability to learn simple control laws, solve inverse kinematics problems, do gain
scheduling, and develop optimal (or nearly optimal) plans, and to adapt to system changes. All these advances can
prove to be of great benefit to UAV applications.
Currently, a data link is needed onboard the UAV in order for the ground operator to maintain continuous
control of the air vehicles. In the future, the UAV will be called upon to perform more complicated tasks and at
greater range and with greater mission endurance. In addition, a single mission control station will be required to
control multiple UAVs simultaneously in order to achieve high rate of mission utilization. The real time data link
solution for required UAV command and control and communication, may proved to be prohibitively complex and
expensive! The greater extent of the UAV autonomous operation will alleviate the UAV data link implementation
problems.
This project seeks to demonstrate the feasibility of using advances in Neural networks to solve autonomous
multiple UAVs command and control problems. Three applications areas are:
1. Can a neural network learn to manipulate a conventional flight UAV or nonlinear system such as helicopter type
UAV maneuvering in turbulent flow, and recover from extreme changes similar to damage and severe meteorology
such as a sudden change of wind on landing, or a change in aerodynamics autonomously?
2. Can a neural network plan an optimal sequence of actions in accomplishing the predefined UAV missions while
reacting and adopting to varying external phenomena using onboard sensors as necessary, such as maneuvering
autonomously to seek out, locate, and maintain track on the targets of interest, and to complete the mission and
return to recovery in a minimum time?
3. Can a neural network schedule and execute multiple autonomous UAV missions simultaneously while adopting
and reconfiguring as needed due to changing external events?
Phase I: Identify and evaluate innovative neural networks control and scheduling concepts that provide
autonomous flight operations and simultaneous mission control of multiple
UAVs. Develop a plan to mature the design concept for later demonstration and generate a simulation model.
Phase II: Develop and demonstrate the simulation model using the JPO provided mission scenarios.
N92-129 TITLE: Vertical Takeoff and Landing Unmanned Aerial Vehicle for Maritime and Close Combat
Applications
CATEGORY: Advanced Development
OBJECTIVE: Develop and demonstrate a safe, high forward speed, vertical takeoff and landing (VTOL) unmanned
aerial vehicle for maritime and close combat applications.
DESCRIPTION: Next generation UAVs will be required to operate safely and efficiently from available deck space
on small surface combatants, and from small clearings or other restricted areas during amphibious close combat
operations onshore. The constraints of limited deck space on most surface combatants, with proximity of above-
deck rigging and other superstructures, will require a true VTOL class air vehicle for launch and recovery. Support
for urban combat and other onshore operations with a mobile landing force also mandates a UAV system which
requires minimum landing and takeoff area, with little or no surface preparation before use. Current VTOL UAV
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designs have inadequate safety features necessary to operate in confined spaces, and most lack the forward
transition speed to rapidly reach a desired target area. The air vehicle design must ensure the safety and protection
of operating personnel and nearby equipment during launch and recovery. This advanced design must also exceed
the forward speed and maneuver capabilities of present VTOL UAVs. Improved forward speed and maneuver
capabilities are required to increase survivability in the anticipated hostile anti-aircraft combat environment. This
forward speed capability must be coupled with appropriate inflight stability, so that the gimbal stabilization
requirement for onboard imaging sensors is minimized. The vehicle gross takeoff weight shall not exceed 400
pounds, with a 100 pound payload (control avionics and sensors) and fuel included. The required radius of
operation is 100 nautical miles, with a desired maximum on-station loiter time of 8 hours. Operating altitudes range
from a hover in ground effect to a minimum in-transit cruise altitude of 10,000 ft AGL. Efficient forward dash
speed operation of at least 90 knots TAS is required, with higher speed desire. Design features for reduced vehicle
radar and infrared signatures are also desired to further increase expected combat survivability.
Phase I: Identify and evaluate innovative concepts that provide a safe, high speed, VTOL unmanned aerial
vehicle for maritime and amphibious close combat applications. Develop a plan to mature the design and
demonstrate a full scale flight vehicle over the entire projected operating envelope.
Phase II: Develop and demonstrate prototype equipment for the air vehicle design proposed under Phase I.
N92-130 TITLE: Improved Air-Delivered Mines
CATEGORY: Engineering Development
OBJECTIVE: To improve the electronics in the GATOR/VOLCANO mines for use in future Navy weapons
systems.
DESCRIPTION: The Navy GATOR is an air-delivered mine system that delivers 45 BLU-91 Anti-Tank and 15
BLU-15 Anti-Personnel mines to deny, disrupt and channelize enemy mechanized forces. The GATOR system was
originally developed in the late 1970's and the mines utilize electronics from that era. While minor improvements
have been made to the mines, they are not state-of-the-art. The GATOR system will go out of production with the
last procurement in FY-93. However, there are planned future requirements to maintain an air-delivered mine
capability. With the advent of so many electronic improvements it would be advantageous to incorporate them into
future editions of these types of mines.
Phase I: Should consist of technological investigation and analysis of those state-of-the-art electronics devices
that would be most feasible and adaptable to GATOR mines and a study report that describes the improvements
offered and the best course of action to incorporate them.
Phase II: Should use the approach outlined in Phase I to design the improvements into the mine and further, to
demonstrate the feasibility.
N92-131 TITLE: 20MM Radiation Hazard(RADHAZ) Primer
CATEGORY: Engineering Development
OBJECTIVE: To provide an initiating device (primer) that will be safe to handle and use in the intense shipboard
electromagnetic radiation environment.
DESCRIPTION: The M52 primer now used in Navy 20MM ammunition is fired electrically in M61A1, M197 and
M39 guns. As a result, the primer presents a radiation hazard (RADHAZ) due to its potential for inadvertent
initiation in the intense electromagnetic environment encountered aboard Navy ships. Previous efforts to counter
RADHAZ have concentrated on shields or attenuators. These have proven successful in larger components but are
not feasible for a small component like the M52. There have been recent efforts at the Naval Surface Weapons
Center, Dahlgren to adopt semiconductor technology into a primer device, but this has been unsuccessful to date.
Phase I: Should consist of technical research and analysis to determine the most feasible and available
technology to adopt into a primer device and a report describing the approach to be used.
Phase II: Should use the approach described in Phase I to design and conduct laboratory demonstration of the
primer device.
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N92-132 TITLE: Multi-Sensor Integration for High Altitude Bombing
CATEGORY: Exploratory Development
OBJECTIVE: Demonstrate feasibility and utility of multi-sensor integration for high altitude targeting.
DESCRIPTION: A major requirement emerging from the Gulf War is the ability to accurately attack ground targets
from high altitudes. The high altitude bombing scenario looks to be a viable tactic reaching well into the next
century. With the advent of new generations of stealth aircraft and internally carried weapon stores the problems of
target acquisition, platform-weapon transfer alignment, and accurate guidance over long ranges becomes more
challenging. Aircraft sensor data will have to be transferred to internal stores prior to launch as weapon sensors will
be shielded behind closed doors. With projected launches from as high as 60,000 feet, GPS or other aiding will be
required to assure adequate IMU accuracy. The tradeoffs between aircraft sensor, weapon sensor, and GPS system
accuracies required for accurate high altitude bombing in the year 2000 and beyond is the subject of this SBIR.
Phase I will consist of a survey of projected state-of-the-art for the required sensors in the year 2000, development
of mathematical models to match projected tactical scenarios, and some basic subsystem tradeoff analysis to
characterize the feasibility of the high altitude bombing concept and establish parameters/accuracy budgets for the
various subsystems. Phase II will involve in-depth studies of the selected optimal configurations, characterization
of the recommended approaches with the model, build-up of basic prototype hardware, and laboratory and field
tests to verify system concepts.
Phase I: Characterization of sensors, development of models, and subsystem tradeoff studies to validate and
optimize high altitude bombing concept.
Phase II: Refinement and optimization of system designs and phase I, buildup of prototype hardware, and
laboratory/field tests to validate the models and verify system concepts. It is expected that this effort will result in a
system specification for the guidance unit to be used by the Advanced Bomb Family for high altitude bombing
application.
N92-133 TITLE: Tooling Concept for the Fabrication of Large, Complex Composite Structures
CATEGORY: Exploratory Development
OBJECTIVE: To develop and demonstrate a durable, dimensionally stable and thermally responsive tooling
concept. If successful, this tooling concept will be used to fabricate large, complex, high quality composite
structures for high performance tactical aircraft.
DESCRIPTION: The size and complexity of unitized composite structures proposed for use in emerging high
performance tactical aircraft requires that a new tooling concept be developed. When applied to new structural
concepts, existing tooling concepts have resulted in excessive manufacturing defects and high scrappage rates. An
acceptable tooling concept should possess the following attributes. First, the tool must possess a low heat mass and
good thermal conductivity and be responsive to computerized process control which will require controlled heat-up
rates, precise dwell intervals and temperature uniformity. Second, the tool must possess excellent dimensional
stability and must provide uniform pressure against the entire surface of the component despite the existence of a
large number of deep integral stiffeners and complex surface contours. Therefore, it must resist creep after repeated
thermal cycling to 400∞F and pressure cycling to 100 psi and must possess a coefficient of thermal expansion
compatible with most carbon reinforced, polymer matrix composites. Third, the tooling concept must possess
excellent durability and wear resistance to withstand repeated usage. Therefore, it must be resistant to scratching,
cracking, embrittlement, puncture, air leakage, and repeated exposures to polymer curing agents and cleaning and
degreasing solvents. Fourth, the tool must be easy to fabricate to the complex shapes and as necessary be amenable
to repair/modification.
Phase I: Should consist of a study outlining various innovative tooling approaches and selection of one or two
approaches which best satisfy the requirements detailed above along with sufficient data to demonstrate feasibility.
Phase II: Should apply the approaches outlined in Phase I to fabricate a representative component and deliver
it to the government for non-destructive and destructive testing and demonstrate durability and repairability.
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N92-134 TITLE: In Situ Process Monitors for Composite Processing
CATEGORY: Exploratory Development
OBJECTIVE: Develop transducer systems which can be used on the surfaces of composite process tools.
DESCRIPTION: The Navy's recent experiences with the processing and fabrication of composite components on
the A-6 and A-12 programs have demonstrated that there are still significant problems with the production of high
quality parts. One of the problems in this technical area is a lack of sufficient information on the state of the
material as a function of the process time/temperature. Specifically, component quality could be improved or at
least reject rates could be minimized if the effect of external process variations on material behavior could be
monitored directly. Conventional sensor concepts have some shortcomings. They act as point sensors and therefore
require some prior knowledge of critical areas for placement. Their presence in the system may affect the
parameters being studied. An alternate approach for sensor systems would be to use piezoelectric films. These
materials have the potential for monitoring both temperature and pressure over the entire surface of the tools used in
production. Also, film transducers can be made extremely them (<1 mil) and applied as coatings. Conventional
transducer materials are limited in application temperature to approximately 200∞F. Materials for aircraft
composite fabrication must be useable at 350∞F. The development of robust tool coatings which could serve as
temperature and pressure sensors would be beneficial for rapid tailoring of the process parameters for the
production of complex components.
Phase I: Of this effort will entail the synthesis and/or formulation of suitable piezoelectric materials.
Phase II: Will entail the scale up of the material, the development of useful poling techniques, the
development of application procedures, and the demonstration of the concept.
N92-135 TITLE: Composite Material Electronic Enclosures and Circuit Module Heat Sinks/Substrates
CATEGORY: Engineering Development
OBJECTIVE: To demonstrate the electronic packaging advantages of reinforced polymer and metal matrix
composite materials (PMC and MMC) with high specific properties in high performance Navy and DoD platforms,
such as the AX aircraft. Properly integrated into the electronic packaging scheme, these material systems will effect
substantial weight savings and increased performance reliability and availability.
DESCRIPTION: Avionics packaging schemes utilizing PMC and combinations of MMC material systems
reinforced with high modules and high strength graphite fibers and silicon carbide particulates and whiskers will
provide specific advantages to the AX program. Reduced avionic weight will provide weight penalty savings.
Enhanced performance and efficiency will be reflected through increased thermal management, tailorable
coefficients of thermal expansion (CTE) and environmental protection (shock, vibration, etc.). Life cycles costs
will be enhanced through improved reliability and maintainability aspects.
Phase I: Should consist of studies and designs that address the requirements of AX program electronic
packaging as related to enclosures and circuit module heat sinks/circuitry substrates. Sufficient data should be
generated to demonstrate feasibility of MMC and PMC materials utilizing high modules and strength graphites and
SIC reinforcements to fabricate electronic enclosures and circuit modules.
Phase II: Should utilize the resultant data to design, manufacture and test deliverable packaging hardware
components to the government.
N92-136 TITLE: Subcooled Liquid Change of Phase Thermal Management for Electronic Packaging
CATEGORY: Engineering Development
OBJECTIVE: To investigate and demonstrate the concept of subcooled liquid change of phase thermal
management for high performance avionic systems. The technique can be effectively utilized in closed systems
applications for circuit and modules and electronics enclosure.
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DESCRIPTION: Change of Phase (COP) thermal management will enhance circuit module performance by
increasing cooling capabilities and reliability. Future avionic systems will employ high thermal density packaging.
As circuit module power densities continuously increase, the need for highly effective thermal management systems
will continue. COP cooling utilizing Subcooled Fluorinert* liquids will provide a method of maintaining a constant
temperature environment within enclosed circuit modules for high and very high thermal densities in high
performance aircraft (and potentially, enclosures). This method will be directly applicable to the AX program. It
will provide a tailored liquid cooling system that features COP and on-site condensation of COP vapor bubbles.
Enhanced with leak proof, quick disconnect liquid connections, the packaging techniques is applicable to integrated
rack concepts (i.e., no specific traditional enclosures) as may be employed by the AX program. A secondary
advantage of this technique is the use of more traditional circuit board materials. Composites, while advised for
enhanced weight reduction need not be exotic, high thermally conductive types. Fluorinert liquids provide high
dielectric strength, are residue-free, nontoxic, very stable, and nonflammable.
Phase I: Investigate and generate studies addressing the design and processing of circuit Modules using the
method of thermal management. Enclosed modules (i.e. such as "clamshell" type) should be utilized for use in
integrated racking as well as traditional enclosures. (*3M Company)
Phase II: Fabricate and test circuit module models deliverable to the government.
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N92-137 TITLE: Military-Grade 3-1/2 inch Rewritable Optical Disk Drive
CATEGORY: Advanced Development
OBJECTIVE: Develop a 3-1/2 inch (90-mm) Magneto-optic REWRITABLE optical disk drive system architected
for operation in harsh environments and designed using mil-spec components.
DESCRIPTION: Currently, optical disks are being incorporated onto aircraft platforms for READ-ONLY, digital
map storage using 5-1/4 inch WRITE-ONCE militarized optical drives. There is a trend in industry and the other
Armed Services to expand the role and move toward a REWRITABLE product. The JIAWG Optical Disk Working
Group is also recommending the use of REWRITABLE technology for future JIAWG aircraft. A 3-1/2 inch optical
drive may provide a better form factor for ruggedized environments, as well as being able to utilize the SEM-E
format for packaging. Data-loader applications could benefit from 3-1/2 inch technology by providing a small,
rugged package capable of storing 128 megabytes of data. The drive would incorporate a digitally adaptive servo
mechanism and electronics to intelligently monitor temperature in order to dynamically recalibrate amplifier gains,
read/write circuitry, and optical elements to maintain optimum performance over extended temperature ranges. The
completed drive would be capable of meeting or exceeding the following baseline specifications:
-20∞C to +71∞C Temperature range
Operating altitude to 80,000 ft
Operation in a vacuum
Shock 30 g's for 11 msec
Operational vibration - 6Grms from 20 to 20,000 Hz
Humidity - 95%
In addition, the drive and the media would support the American National Standards Institute (ANSI) 90-mm,
128 Mbyte, M-O, continuous-composite-grooved Standard currently under development. The drive would be
supplied with a SCSI interface, cables, interface adapter card, suitable power supply, and driver software. The drive
would be packaged into a SEM-E module and have a comprehensive built-in-test (BIT) function.
Phase I: should consist of an investigation of technology-status of suitable digitally adaptive electronics, and a
plan to modify and/or design a 90-mm MO deckplate for use in military optical disk systems.
Phase II: should consist of fabrication of a mechanical transport with adequate anti-shock housing and
vibration isolation system. Provide mechanical integration and mechanical integrity tests. Also a complete
electronic system design consisting of controller and READ/WRITE electronics, optical head and servo system
should be provided. Thorough environmental testing should be accomplished on the completed unit (shock,
vibration, thermal, etc.) with delivery of two prototype flight systems, ten media, test reports, instruction manuals,
and other documentation.
N92-138 Title: NDI Technique for Galvanic Degradation of Composites
CATEGORY: Advanced Development
OBJECTIVE: The development of a nondestructive inspection technique (NDI) which will provide quantitative
information on the severity of galvanic induced degradation of composites.
DESCRIPTION: Recent efforts have demonstrated that there is a potential for galvanic-corrosion induced
degradation in graphite/polyamide (gr/PI) composites. The Navy is concerned that this degradation will impact
structural performance. This is a prime consideration for material selection for emerging aircraft. There is the
potential that gr/PI material will be selected for particular components which require lightweight construction. It
would be beneficial to have some means to detect and track any galvanic degradation in these composites so that
appropriate maintenance actions could be performed.
Phase I: Should consist of a study of appropriate, novel NDI techniques which can be used to detect the
degradation which has only been observed to date with destructive microscopic procedures. Correlations between
signal and structural significance of the defect should be performed.
Phase II: Should entail the development of the NDI system and demonstration under field and depot level
conditions.
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N92-139 TITLE: Application Equipment/Software for Multi-Layer Fuel Tank Coatings
CATEGORY: Engineering Development
OBJECTIVE: To apply and control the application of multi-layer seal coatings on all surfaces of integral fuel tanks.
If successful, this materials application control system would decrease production costs, reduce aircraft weight,
increase fuel capacity and improve reliability.
DESCRIPTION: The complexities of aircraft fuel tank and vent spaces present a real challenge when applying
functional coating to seal the fuel liquid and vapors. Coatings must be applied layer by layer to allow solvents,
water vapor and/or reaction products to escape to prevent void formation and leakage. In addition, coating
thicknesses must be varied in different areas for stress compensation and other factors. The nozzle of applicator
must be attached to an arm with six degrees of freedom to reach all surfaces in complex interior tanks. Since
multiple layers of coating are applied the controlled nozzle device must be able to retrace and/or modify its path
several times. Feedback must be used to both record (and/or observe) and control coating thicknesses. A
computerized device with appropriate software programs is needed. The system must also include proper mixing,
heating, pressure feed and vapor control equipment.
Phase I: Should consist of a study outlining the approach which will be undertaken to pursue the requirements
addressed above with sufficient data to demonstrate feasibility. The study should also address the selection of the
coating material or materials that will be used to demonstrate the application and control system.
Phase II: Should use the approach outlined in Phase I to develop the complete system and deliver to the
government or a selected agent of the government for demonstration proposes.
N92-140 TITLE: Composite Embedded Optical Fibers for Communication Links
CATEGORY: Engineering Development
OBJECTIVE: To extend and explore the "smart skins/structures" concept of embedded optical fibers in lightweight
composite material structures with high specific properties for avionic modular packaging to achieve avionic and
intra-aircraft communications. This concept will employ embedded optical fibers as primary communications paths
within avionic enclosure and circuit module structures. Employed in high performance aircraft, such as the AX, this
technique will affect high signal transmissions, reduce weight, eliminate electromagnetic interference, and reduce
crew work loads.
DESCRIPTION: Future aircraft will incorporate embedded sensors and computer networks to monitor flight loads,
environmental stresses, aircraft structural integrity, and hostile threats. Responses to these monitored functions will
initiate corrective actions and achieve real time reconfigurations of controls and post-flight repair and maintenance.
The concept of embedded optical fibers for intra-aircraft communication of signals within the smart skins/structures
and within intra-connected avionic systems. System inter-connections utilizing signal tapping and evanescent
coupling will be employed.
Phase I: Will generate studies and designs addressing the processing of optical fibers in Polymer and Metal
composites (PMC and MMC) and methods for interconnecting panels in both in-line and orthogonal attitudes.
Phase II: Should utilize resultant studies and designs to demonstrate embedded and interconnected panels and
an enclosure encompassing interconnected "circuit modules". Vibration, shock and thermal cycling tests should be
used to demonstrate applicability to the AX environment. Circuit module models should demonstrate
disconnect/reconnect.
N92-141 TITLE: Formulation of Effective Corrosion Scavengers
CATEGORY: Exploratory Development
OBJECTIVE: Develop coating systems and/or additives which will mitigate degradation of composites and metal
alloys due to galvanic interactions.
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DESCRIPTION: Galvanic degradation of metals and imide based composites has been found in aircraft materials
combinations. Protection schemes have been developed, and have been documented, to provide adequate insulation
and reduced corrosion rates. At this point, there has been no long term study of the effect of the galvanic
interactions on structural performance. Further, these schemes require strict adherence during manufacturing. The
Navy has experience with manufacturing deviations during production which have compromised the isolation
schemes. It would be beneficial for structures on emerging aircraft systems to increase the level of confidence in
the use of potentially galvanic material couples. An approach towards accomplishing this goal would be to develop
effective scavengers which would interfere with the degradation process. NADC has extensive experience with the
implementation of quartenary amine salt complexes which have been demonstrated to reduce corrosion rates under
specific conditions.
Phase I: Of this effort would be the formulation of novel scavenger systems which will be specifically
designed for the galvanic degradation process of interest. The effectiveness of these systems in the reduction of
corrosion rates will be examined.
Phase II: Of the study will entail some scale up and the development of practical carrier systems which will
allow the application of these scavengers as a routine maintenance activity.
N92-142 TITLE: Localized Sensor System for Damaged Metallic Aircraft Structure
CATEGORY: Exploratory Development
OBJECTIVE: Develop a localized sensor system (adaptable to Navy aircraft) to sense cracks in metallic structures
and provide information to maintenance personnel indicating the existence of a crack is present and severity of the
crack.
DESCRIPTION: Today's aircraft are susceptible to cracking of metallic structural components which can lead to
failure of the aircraft. At present, analysis and inspection are the methods used to predict and observe crack
initiation and growth. When a crack is found in one aircraft, many aircraft are often grounded because they may be
susceptible to the same type of crack. Rather than grounding all of these aircraft, a sensor system needs to be
applied to the location where the crack is most likely to occur. Such a sensor system will sense crack initiation and
monitor growth in real time. The system will provide an easy to access method to monitor the status of the structure
upon completion of flight (i.e., no crack, crack initiation, and crack exceeds allowable values). The monitor must
not be sensitive to any other source that could cause a faulty interpretation of crack size.
Phase I: This portion of the program will be develop the crack sensor system and demonstrate it in a
laboratory atmosphere.
Phase II: It will be necessary to design a package for the device that can be certified for usage on Navy
aircraft. It will also be necessary to demonstrate the device on an actual aircraft.
N92-143 TITLE: Evaluation of a Fault Coverage Methodology for Digital Modules
CATEGORY: Advanced Development
OBJECTIVE: To perform an evaluation of a fault coverage metrics methodology for digital modules that was
developed by a JIAWG Diagnostic Initiative in FY-91. Multiple independent evaluations are required using the
same test case to verify that the methodology is useable and repeatable. Since JIAWG common modules will be
built by different vendors and are required to be interchangeable, it is critical that a common method be developed
to accurately and consistently derive and measure module fault coverage metrics. If successful, this will provide the
government with an evaluation tool for effectively verifying vendor designs which are currently unverifiable. In
addition, this methodology could be used in the JIAWG module certification process.
DESCRIPTION: The JIAWG Diagnostic Initiative developed a methodology, Reference (a), to derive fault
detection, fault isolation coverage, failure latency, and false alarm rate metrics. The methodology use logic
simulation for verifying the metrics and VHDL (VHSIC Hardware Description Language) for describing module
functionality.
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Phase I: Three different vendors will participate in independently evaluating the methodology described in
Reference (a) be applying it to the same test case. The test case will be jointly selected by the three vendors and
government JIAWG representatives. Vendors should propose simple but meaningful test cases for digital functions
as candidates for verifying the methodology. Each participating vendor shall provide a final report describing the
steps used in applying the methodology to derive the metrics, observations, conclusions, and, if necessary,
recommendations for improving the methodology. The government will then use the results to assess the validity
the methodology.
Phase II: Depending on the results of Phase I, Phase II will either use the Phase I data to revise and/or refine
the methodology or apply the methodology to a more complex case consisting of an entire module selected by
JIAWG.
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N92-144 TITLE: Improved Capability Electronic Ejection Sequencer (ICEES)
CATEGORY: Engineering Development
OBJECTIVE: To save the lives and reduce injuries of crewmembers who eject from multi-place jet aircraft during
out-of-control and high speed ejection conditions.
DESCRIPTION: Aside from determining what mode of ejection sequencing events would have to occur during and
ejection, ICEES would also have to (1) determine where the other ejected sears are located in spatial reference to
each other, (2) signal other seats as to where in space they are located, and (3) send signals to the thrust vector
control system of its own seat to properly guide it through the ejection sequence.
Phase I: Should consist of (1) identifying what inputs and outputs would be required of the electronic
sequencers in a multi-seat ejection scenario and (2) addressing how the
components could be tested without undergoing actual ejection tests.
Phase II: Should consist of the fabrication of a testable prototype and, in accordance with the with the
approach outlined in Phase I, testing to demonstrate feasibility.
N92-145 TITLE: Innovative Design for Aircraft Canopy Fracturing System
CATEGORY: Exploratory Development
OBJECTIVE: To develop a new canopy fracturing method that can fracture thicker canopy acrylic without
producing excessive noise and debris.
DESCRIPTION: Current canopy fracturing designs mount the detonating cord on the interior periphery of the
canopy acrylic and sometimes over the aircrews heads. This placement obstructs vision, exposes the detonating
cord to damage and produces excessive noise and fragments when detonated. This method is also unacceptable on
laminated canopies and canopies with thicker and tougher acrylics. A better method of canopy fracturing could
allow fracturing of laminated canopies or thicker acrylics. The aircraft canopy design is usually lighter and less
expensive when canopy fracturing is used for the escape path clearance. Also, escape systems using canopy
fracturing do not need to delay seat ejection, as does a system which jettisons the canopy.
Phase I: Should consist of a study to recommend an approach to pursue the requirements addressed above
with sufficient data to demonstrate feasibility.
Phase II: Should use the approach from Phase I to design or procure detonating cord for use in fracturing
demonstrations.
N92-146 TITLE: Life Cycle Cost (LCC) Oriented for Naval Aircraft
CATEGORY: Engineering Development
OBJECTIVE: Provide a Life Cycle Cost (LCC) analysis program which includes better input parameters taking
into consideration the Navy deployment scenario of carrier operations and support. This will ensure that LCC
influences on system design are comprehensive and provide accurate estimates to support each cost significant
management decision.
DESCRIPTION: LCC is defined as the total cost of an item or system over its full life. It includes the cost of
acquisition, ownership (operation, maintenance, support, etc.) and where applicable, disposal. To be meaningful,
LCC must be placed in context with the cost elements identified, period of time covered, assumptions and
conditions applied, and whether it is intended as a relative comparison or absolute cost estimate. The purpose of
this project is to better define input parameters which take into consideration Navy operational environment and
unique support requirements necessary for carrier deployments. Input parameters should address all the Integrated
Logistics Support (ILS) elements. Operations and support cost data is often initiated during program phases when
not much data is available. As better data becomes available LCC estimates are refined, resulting in better decision-
making criteria.
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Phase I: Should consist of a study outlining the approach which will be taken to provide a more
comprehensive LCC analysis model, which include parameters associated with Navy operational requirements
addressed above, with sufficient data to demonstrate feasibility.
Phase II: Should use the approach outlined in Phase I to develop an MS-DOS compatible PC LCC model with
necessary documentation and deliver it to the government for testing.
N92-147 TITLE: Spares Forecasting
CATEGORY: Engineering Development
OBJECTIVE: To provide a method to forecast the quantity of repairable spares which are lost due to attrition in
sufficient time to provide lead time for replenishment.
DESCRIPTION: Spares are purchased in sufficient quantity to allow a pipe line of units while defective units are in
the repair cycle. There is currently no method to determine how many spares are lost due to attrition (i.e. damage
beyond repair, repair exceeding engineering tolerances). The purpose of this project is to develop a means to
forecast/document attrition rate with sufficient lead time for replenishment to prevent excessive downtime from lack
of spares.
Phase I: Should consist of a study outlining the feasibility of developing a data feedback system to forecast
replenishment requirement not evident from usage monitoring.
Phase II: Should develop prototype system for forecasting/documenting attrition rate.
N92-148 TITLE: Environmentally Degradable Chaff Packaging
CATEGORY: Advanced Development
OBJECTIVE: Develop an environmentally degradable material which can be formed into a container for chaff.
DESCRIPTION: The environmentally degradable material will be used to produce chaff packets compatible with
the D-46/ALE-39 Countermeasures Chaff Dispenser. The packet will house approximately 1 1/2 ounces of chaff
and be interlocked into a set of 16. This set must be capable of withstanding normal handling, not deform/deflect
when subjected to an acceleration of 8-9 "G's" or when subjected to sub-sonic airflow indirectly impinging on its
rear surface when housed in the dispenser. Additionally, the packets must be frangible to the extent that they will
disintegrate upon contact with a metal, metal laminate, or fiber laminate surfaces at 100 knots.
Phase I: Deliverables shall be a final report and 16 packets made of the material to be subjected to normal
handling. Specific dimensions of packets to be provided upon contract award. Approximate measurements 2 1/2"
x 3 1/4" x 1/3".
Phase II: Deliverables shall be a final report and 20 sets (320 packets) which will be subjected to U.S. Navy
funded ground and air tests.
N92-149 TITLE: Infra-red Image Processing Using Fuzzy Logic Expert System Technology
CATEGORY: Exploratory Development
OBJECTIVE: Develop advanced infra-red image processing techniques for noise reduction, image enhancement,
and band width reduction/image compression based on fuzzy concepts.
DESCRIPTION: Optimal processing of infra-red imagery for weapon seeker applications depends on a good
understanding of the structure of the image being processed. A practical complex scene model for infra-red images
would facilitate processing of those images. Model development depends on an iterative sequence of steps of
analysis, hypothetical models, hypothesis testing, model refinement, and final definition of the model. An expert
system based fuzzy logic could facilitate the development of complex scene models which would not be dependent
on exact parameters. The problem is to develop and demonstrate such an expert system, supply it to the
development of a complex scene model for infra-red images and then use the complex model to develop techniques
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for noise reduction, image enhancement and bandwidth reduction/image compression for transmission and storage.
The image processing techniques would then be reduced to integrated circuit chips for tactical application.
Phase I: Feasibility study to demonstrate application fuzzy logic in the development of an expert system for
military infra-red image processing applications.
Phase II: Complete development of expert system, complex scene modeling and image processing techniques.
Reduce algorithms to integrated circuit scale chip set.
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N92-150 TITLE: Air ASW Acoustic Classification
CATEGORY: Advanced Development
OBJECTIVE: To establish algorithms for classifying active acoustic contacts.
DESCRIPTION: ASW in the current post cold war environment is expected to be regional in nature with emphasis
on small quiet targets. ASW operations under these conditions are expected to require active systems with all
associated problems. One driving issue with active sensors is active classification of contacts as sub/non-sub or
class of target. This SBIR task is intended to provide algorithms for active classification and to test those
algorithms in simulated environments. The required tasks are:
Phase I: Identify techniques used currently in air, surface and sub-surface systems for active classification.
Define active classification algorithms with potential for providing high probability of classification. Identify
existing recorded data collected during fleet operations that may be used to test the algorithms. Define a
methodology to prepare simulated recordings of active returns in a realistic background for use in algorithm tests.
Define a process to use the fleet data or simulated data to test the algorithms using fleet operators.
Phase II: Prepare a simulated recording of active signal returns in a realistic background. Conduct an
experiment using fleet operators with the simulated recordings to test the algorithms proposed in phase I and other
algorithms that show promise. Prepare documentation describing the algorithms showing benefits and deficiencies
of each.
N92-151 TITLE: AH-1W Improved Ballistic Tolerance
CATEGORY: Advanced Development
OBJECTIVE: Locate areas on the AH-1W susceptible to ballistic damage caused by ground and fixed-wing/rotary-
wing aircraft fire. Identify areas susceptible to ballistic damage that pose the greatest threat to aircraft/aircrew
survivability. Explore technologies that can be integrated within the current airframe that will provide increased
survivability to aircraft/aircrew from ballistic damage. This effort should take into
consideration technologies that minimize aircraft weight growth, provide cost effective solutions, and allow for
retrofit.
DESCRIPTION: The U.S. Marine Corps, through new development and a block modification program, will
achieve an all AH-1W helicopter fleet in the early 1990's. This aircraft will be a front-line attack helicopter well
into the next century and must remain capable of meeting the threat. The increasing threat from ground and fixed-
wing/rotary-wing aircraft has given rise to the need for developing new state-of-the-art technologies that will
increase survivability of aircraft/aircrew. Technologies developed should take into consideration the following: 1.
Cost effectiveness; 2. Improving aircraft ballistic tolerance; 3. Improving aircrew ballistic tolerance; 4.
Minimizing weight growth or reducing aircraft weight; 5. Ease of retrofit into the aircraft; 6. Advances in materials
research.
This effort shall consist of a design study exploring the incorporation of the improvements discussed above and a
conceptual design of improvements in aircraft/aircrew ballistic tolerance, including a mock-up.
N92-152 TITLE: AH-1W Improved Crashworthiness
CATEGORY: Advanced Development
OBJECTIVE: Identify aircraft areas that are likely to cause aircrew injury and death in a crash situation. Explore
technologies that can be integrated within the current airframe that will provide increased survivability of aircraft
and aircrew in the event of a crash and possible post-crash fire. This effort should take into consideration
technologies that minimize aircraft weight growth, provide cost effective solutions, and allow for retrofit.
DESCRIPTION: The U.S. Marine Corps, through new development and a block modification program, will
achieve an all AH-1W helicopter fleet in the early 1990's. This aircraft will be a front-line attack helicopter well
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into the next century and must remain capable of meeting the threat. Danger in the event of an aircraft crash and
post-crash fire has given rise to the need for developing new state-of-the-art technologies that will increase
survivability of aircraft and aircrew under these circumstances. Technologies developed should take into
consideration the following: 1. Cost effectiveness; 2. Improving aircraft crashworthiness; 3. Improving aircrew
survivability of a crash; 4. Minimizing weight growth or reducing aircraft weight; 5. Ease of retrofit into the
aircraft; 6. Improving aircrew survivability of a post-crash fire; 7. Reducing the possibility of a post-crash fire.
This effort shall include a design study exploring incorporation of the improvements discussed above and a
conceptual design of improvements in aircraft and aircrew crashworthiness, including a mock-up.
N92-153 TITLE: Visualization and Analysis for Cruise Missile
CATEGORY: Advanced Development
OBJECTIVE: Development of innovative techniques for visualization.
DESCRIPTION: Visualization, the technique of combining both image processing and graphic techniques, has
strong potential in mission planning, preflight and post-flight evaluation, and training. For many DOD applications,
visualization must use data Sources such as maps, photographs and video data. Processed data is often enhanced by
adding graphics or multi-dimensional (volume) rendering and photo-realistic rendering.
Phase I: Effort under this topic, & feasibility study and preliminary design should be completed. The study
should address data sources, innovative visualization techniques and final products. The preliminary design should
include the data and human interface as well as hardware and processing algorithms. Both timeliness and flexibility
in a workstation
environment should be stressed. A report should then be submitted.
Phase II: The effort should be directed to the completion of the design and algorithm development. These
then should lead to a demonstration/test using various data input sources, image processing techniques, and
rendering for evaluation of test missions and training.
It is anticipated that the architecture and algorithms developed under this SBIR will have immediate
acceptance for both DOD and commercial use.
N92-154 TITLE: Terrain Contour Matching (TERCOM) Map Placement
CATEGORY: Exploratory Development
OBJECTIVE: To improve the probability that a TERCOM map can be constructed and will actually enhance
routing success before requesting that a map actually be constructed.
DESCRIPTION: There are no automated tools available to help a cruise missile mission planner determine suitable
TERCOM sites. A planner may be able to determine the general area in which a map is needed, but not whether or
not the map, once produced will be viable. A proof-of-concept of an approach that combines map construction
rules, terrain analysis, and route planning placement requirements is sought.
The concept for map placement should support 2 modes: 1) requesting TERCOM maps to support a particular
mission or set of missions, and 2) requesting TERCOM maps to populate a new scenario before specific mission
tasking exists. The mission specific mode should be robust enough to support both automated planner assistance
and completely automated modes of operation. The non-mission specific mode should assist in determining if map
availability is even a problem before TERCOM maps are requested.
Phase I: Should consist of determining the feasibility of the proposed approach for identifying suitable areas
for map construction. Phase I should be accomplished by engineering assessment, development of a concept of
operations, and the application of off the shelf commercial rapid prototyping tools as appropriate. The preference is
for all electronic products and documentation.
Phase II: Would be the actual development of a prototype that supports the entire concept of operations in a
reusable software module.
N92-155 TITLE: Minimum Simulation Cues Required for the Rotorcraft Shipboard Landing Task
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CATEGORY: Advanced Development
OBJECTIVE: Determine the minimum simulation cues required for helicopter shipboard landing training and for
developing Dynamic Interface (DI) launch/recovery envelopes.
DESCRIPTION: Rotorcraft shipboard landing task simulation requires a satisfactory level of fidelity of each
simulator component. The components include aircraft math model, environmental models, simulator visual
system, motion system, cockpit, associated computers, and component integration. The visual system includes
factors like field-of-view, resolution/texture, and dynamics. Motion system factors include motion onset cues, sus-
tained cues, and washout cues. Environmental models include the ship airwake and ship motion. The aircraft math
model must have satisfactory levels of flying qualities and performance fidelity. A systematic study is needed to
help quantify the minimum levels of fidelity required for each factor associated with simulating the rotorcraft/ship
landing task. Rotorcraft/shipboard landing simulation fidelity should be evaluated in terms of fleet pilot training
and in terms of supporting NATC DI flight testing.
Phase I: Review and document previous work to quantify the level of fidelity of rotorcraft/ship landing
simulations. Consider the overall task, and the individual factors making up each component of the simulation task.
Develop a proposal to quantify the fidelity of the individual factors making up each component of the rotorcraft/ship
landing task.
Phase II: Conduct an experiment using the NATC Manned Flight Simulator (MFS) and a specified rotorcraft
model (H-2, H-60, or V-22). Use additional equipment as required. Quantify the level of cues required for
performing the aircraft/shipboard landing task. Document cue level requirements for fleet pilot training and for
supplementing DI flight testing at NATC.
N92-156 TITLE: Flight Test Instrumentation to Measure the Aerodynamic Flow Field of an H-60 Helicopter
CATEGORY: Exploratory Development
OBJECTIVE: Develop flight test instrumentation to measure accurate airspeed and aerodynamic flow field data
for an H-60 helicopter in hover, low-speed, and forward flight.
DESCRIPTION: Helicopter aerodynamic flow field data are important in aircraft design, test, and simulation. The
flow field is a function of aircraft type and the aircraft flight condition. A sensor is needed to scan the flow field
and record accurate 3-D flow data with a minimum air-volume sample size (less than the main rotor cord). The
sensor should be capable of scanning beyond the H-60 rotor radius. The package should be minimum size and able
to withstand the harsh environment of a helicopter.
It should also be easily installed and easily calibrated.
Phase I: Design a sensor to measure accurate 3-D airspeed and aerodynamic flow data for the H-60
helicopter. Also, design the interface to mount in an H-60 aircraft and provide connectivity to on-board data
packages. Provide a safety, reliability, and accuracy study for the equipment.
Phase II: Build and calibrate the test equipment. Conduct a ground test. Support installation, calibration, and
flight testing in a specified H-60 helicopter. Demonstrate the equipment installation in other available helicopters at
NATC.
N92-157 TITLE: Flight Simulation Domain Model for Reusability
CATEGORY: Advanced Development
OBJECTIVE: Develop the process for domain modelling (generic requirements and dependency diagrams) for the
reusability for the flight simulation software.
DESCRIPTION: In the past, flight simulation/training systems have been acquired through primes and/or through
subcontractors with reusability as one of the requirements in the contract with the intention of reusing the code only.
However, no serious effort has been made in understanding the ramifications of the methodology which promotes
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the software reusability at early stages of the life-cycle. There is definitely a need for understanding the process for
the software reusability which will be used in development of the next generation of flight simulation systems.
Phase I: Phase I study will provide the basic understanding of the Domain Model for the Flight Simulation
Domain for the reusability and provide the rationale its development.
Phase II: Phase II will undertake the development of the software architecture and provide a framework for
implementation of systems in the flight simulation domain based on the outcome of the Phase I results.
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N92-158 TITLE: "Virtual" Air Intercept Control (AIC) Architecture for Training Air Intercept Control Procedures
CATEGORY: Exploratory Development
OBJECTIVE: Develop a simulated flight environment using Artificial Intelligence (AI) techniques to provide
aircrews with automated, no "instructor-in-the-loop" training in (AIC) coordination procedures.
DESCRIPTION: Currently, AIC training, when conducted in flight simulators, requires an instructor or another
aircrew member to portray the role of air intercept controller often under-utilizing that individual's time/effort. This
research effort would investigate the use of AI software as a substitute for actual instructors/crewmembers in flight
simulators and develop an architecture which would permit flightcrews to practice AIC coordination procedures in a
simulated flight environment with a "virtual" air controller.
Phase I: Review the feasibility of using AI techniques to create a "virtual AIC controller and identify a
specific training device which could serve as a testbed for the implementation and evaluation of "virtual" AIC
training.
Phase II: Adapt the AI concept to the selected training device architecture and evaluate the benefits of
conducting AIC procedures training with a "virtual" air controller. Make recommendations on expanding
development and use of "virtual" participants in other flight simulators and other training environments (C3I, tank
warfare, etc.).
N92-159 TITLE: Environmental Degradation Model for Infrared Acquisition and Tracking
CATEGORY: Advanced Development
OBJECTIVE: Develop environmental degradation algorithms for PC- based simulation of infrared (IR) acquisition
and tracking.
DESCRIPTION: If PC-based trainers for the Maverick and SLAM missiles are to provide realistic aircrew training,
graphical depiction of IR imagery through varying visibility conditions--as observed by aircrews--must be
incorporated into the PC-based training system design. Training concepts such as the use of Digital Video
Interactive (DVI), Compact Disc Interactive (CDI), and VCR integration provide means for replaying IR missions.
However, these methods are costly, hardware intensive, and provide limited opportunity for dynamic simulation of
aircrew functions during degraded environmental conditions. Research is required to establish whether degrading
IR conditions can be modeled and presented on PC's in such a way as to ensure realistic aircrew training.
Phase I: Produce a Feasibility Report discussing if modelling is possible for simulating degrading IR
environmental conditions. Included in the report is a discussion of the additional hardware required for supplying
realism to the aircrew when using the modelling on PC-modelling on PC-based training systems.
Phase II: Implementation of the modelling and companion hardware into the PC-based Maverick and SLAM
missile training systems.
N92-160 TITLE: FLIR Training System
CATEGORY: Engineering Development
OBJECTIVE: Develop a Part task trainer/Computer based trainer or Interactive Courseware trainer that will teach
the basic theory of thermal imagery for today's forward looking infrared (FLIR) sensors (AN/AAQ-16, AN/AAS-
38, AN/AAR-50, all versions), interpretation of sensor and thermal scene variables and determine when
employment of Night Vision Goggles is recommended. Training should include optimal and minimal atmospheric
and environmental conditions and there effects on thermal imagery . Additionally, should address both rotary and
fixed wing HUD integration and effects on Night Vision Goggles, if any that pilots need to consider.
DESCRIPTION: Development of a system that will teach basic thermal imagery, interpretation of sensor and scene
variables (i.e. mountains, deserts, water, snow) to determine optimal and minimal conditions for employment of
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FLIR (to include differences between Targeting and Navigational FLIR) verses Night Vision Goggles or integration
of all, teach basic environmental effects (i.e. time of day, change in temperature of environment and how it effects
the temp. of potential target/s,). Teach pilots elementary target identification through heat signatures of potential
targets (i.e. temp. of tank turret before and after firing, potential countermeasures to shield heat of target/s). Teach
pilots/NFO's sensor efficacy (black hot vs. white hot, degrees of FOV for target acquisition) and limitations or
possible illusions.
The system should develop individual training software and thermal scenes to address the specific aircraft's
capabilities/missions. Such considerations should include but not be limited to: ingress and egress altitudes, speeds
of specific aircraft, radar integration/capability if actively interrogating a target.
Phase I: Deliverable will be a final report showing the approach used to determine the requirements and
instruction methods to include recommended media selection.
Phase II: Deliverable will demonstrate selected hardware and software/courseware and show how actual
thermal scenes/imagery will be utilized or demonstrate thermal fidelity on selected hardware. Additionally, will
assess the feasibility of integrating this capability into existing Night capable aircraft simulators. VX-5, MAWTS-1
or HMX-1 will be the potential testing sites.
N92-161 TITLE: Determination of Actual Eye-point in the E-2C Cockpit
CATEGORY: Engineering Development
OBJECTIVE: Determine the actual eye point used by fleet pilots in order to facilitate placement of tactical displays
and flight instrumentation in the existing cockpit structure.
DESCRIPTION: The E-2 program is considering the use of flat panel technology in place of the standard cockpit
instrumentation currently in use. The eye-point actually used by fleet pilots today, as opposed to the eye point
designed to over thirty years ago, needs to be understood so that placement of instrumentation and controls can be
determined. Such information will also be necessary to determine whether the current flight controls will have to be
modified or replaced. Companies wishing to respond to this request will need access to fleet pilots at NAS Norfolk
or NAS Miramar and access to an aircraft cockpit for measurements.
Phase I: Complete research necessary to understand how flat panel displays are used and what human factors
parameters are useful. Identify applicable references and MIL-SPECs. Summarize the research in a format
applicable to the E-2C and present it in a report.
Phase II: Expected deliverables (in report format)
- anthropometric data based on fleet E-2C pilots
- determination of eye-point in a format useful for instrumentation design and placement
- data showing how much of the current flight instrumentation is obstructed by the flight controls
N92-162 TITLE: Determination of cockpit tactical display controls
CATEGORY: Engineering Development
OBJECTIVE: Determine the optimal set of controls necessary to control tactical and flight displays in the E-2C
cockpit from existing military and civilian technology.
DESCRIPTION: The E-2 program is considering the use of flat panel technology in place of the standard cockpit
instrumentation currently in use. The primary purpose of the flat panels is for the pilots to contribute to the mission
by observing tactical information similar to that presented to Naval Flight Officer (NFO) operators in the CIC
compartment aft of the cockpit. The cockpit doesn't permit use of displays like those used by the NFOs, but a
method will have to be determined to allow the pilots to access tactical, flight attitude and navigation information.
Phase I: Survey existing military and civilian controls technology and recommend at least three alternatives
and the rationale used to select them. Present the results in report format.
Phase II: Design and conduct human factors experiments to prioritize selected control alternatives using the
existing
E-2C cockpit as a baseline. Present the results in report format.
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N92-163 TITLE: Flat panel display technology for the E-2C Cockpit
CATEGORY: Engineering Development
OBJECTIVE: Determine what type of CRT and/or flat panel technology is available in the commercial market that
could be retrofit for use in the E-2C cockpit.
DESCRIPTION: The E-2 program is considering the use of flat panel technology in place of the standard cockpit
instrumentation currently in use. The primary purpose in this effort is to provide tactical information to the pilots in
a format similar to that presented to NFO operators aft of the cockpit, thereby allowing the pilots to contribute
directly to the mission. A thorough search of the commercial market to determine existing and planned display
technologies is necessary to determine how best to select one display technology over another. Consideration of
supportability is important and display placement should be understood when selecting display formats.
Phase I: Survey existing military and civilian displays technology and recommend at least three alternatives
and the rationale used to select them. Present the results in report format.
Phase II: Design and conduct human factors experiments to prioritize selected displays alternatives using the
existing E-2C cockpit as a baseline. Recommend display placement, formats and use of colors. Present the results
in report format.
N92-164 TITLE: Use of Heads Up Displays in the E-2C Cockpit
CATEGORY: Engineering Development
OBJECTIVE: Determine whether a "virtual" improvement in E-2C aircraft handling qualities can be achieved by
having the pilot use a heads up display (HUD).
DESCRIPTION: The E-2C aircraft has traditionally been difficult to fly, especially in the carrier environment.
Anticipated increases in mission duration if an inflight refueling probe is installed on the aircraft necessitate
consideration of technologies that will relieve pilot work load, increase safe handling and possibly allow a "virtual"
improvement in aircraft handling characteristics without changing control laws or implementing engineering
changes to the airframe.
Phase I: Survey existing military and civilian HUD technology to determine what might be available for use
in the existing E-2C cockpit without major airframe interruptions. Select at least three candidate systems with
rationale and present in report format.
Phase II: Using existing E-2C flight characteristics, design experiments that will show whether improvements
in handling characteristics can be achieved using a heads up display. Using these results, select the best candidate
system from those chosen in Phase I. Present the results in report format.
N92-165 TITLE: Long Duration Missions on the E-2C Aircraft
CATEGORY: Engineering Development
OBJECTIVE: Determine whether E-2C missions conducted beyond the tradition four to five hour duration have
detrimental effects on aircrew performance.
DESCRIPTION: The E-2C program is considering the installation of an inflight refueling probe in order to extend
the range and endurance of the aircraft. In order to establish limits on the number of hours an E-2C aircrew should
remain airborne, research is needed to determine the effects of current fatigue inducing factors and to determine
whether fatigue relieving procedures or enhancements can be incorporated on the aircraft.
Phase I: Determine what factors are the greatest contributors to aircrew fatigue in the current configuration of
the E-2C. With that data, establish a maximum recommended flight duration. Present results in report format.
Phase II: Determine what procedures or technologies could be incorporated on the E-2C to relieve fatigue and
allow an extension of the maximum recommended flight duration. Present results in report format.
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N92-166 TITLE: Use of Helmet Mounted Displays on the E-2C
CATEGORY: Engineering Development
OBJECTIVE: Determine whether helmet mounted displays (HMDs) can be used by the E-2C pilots for tactical and
flight information.
DESCRIPTION: The E-2 program is considering the use of flat panel technology in place of the standard cockpit
instrumentation currently in use. The primary purpose in this effort is to provide tactical information to the pilots in
a format similar to that presented to NFO operators aft of the cockpit, thereby allowing the pilots to contribute
directly to the mission. The cost of such a conversion could be very high, however, and feasible alternatives should
be explored. HMD technology is making rapid advances but its use in an E-2C type cockpit needs considerable
development.
Phase I: Survey currently available HMD technologies and research HMD advances in work that might be of
value to the E-2C. Assuming HMDs are a technically viable alternative to flat panel displays, establish a
cost/benefit comparison of HMDs vs flat panel conversion. Present results in report format.
Phase II: Design and conduct experiments using HMDs to present E-2C tactical data in a cockpit
environment. Evaluate its effectiveness in both the tactical and flight modes of operation. Present results in report
format.
N92-167 TITLE: Engineering Economy Analysis of an Intercommunication System Conversion for the E-2C
CATEGORY: Engineering Development
OBJECTIVE: Conduct a cost/benefit analysis of converting the E-2C Intercommunication System (ICS) to an
updated system.
DESCRIPTION: The current E-2C ICS system is costly to maintain and inadequate for expanding operational
needs. In the current funding climate, all proposed changes to the aircraft must be justified on more than
operational need.
Phase I: Using the life cycle cost of other new systems available for military aircraft, determine if a new ICS
would be cost effective for the E-2C.
Phase II: Provide three recommendations for alternative systems that can be used to provide ICS capability.
NAVAL SURFACE WARFARE CENTER
N92-168 TITLE: ECM Payloads for UAVs
CATEGORY: Exploratory Development
OBJECTIVE: Develop an Anti-ship Missile Defense Payloads for UAVs.
DESCRIPTION: The Navy has a requirement for cost effective electronic countermeasures (ECM) payloads for
deployment onboard planned Unmanned Air Vehicles (UAV) to enhance the Anti-ship Missile Defense (ASMD)
capabilities of surface ships. The payloads need to be effective against a wide variety of radar and infrared (IR)
guided threat missiles and against the targeting radars of enemy aircraft. The command and control of the ECM
payload needs to provide the capability to coordinate the ECM payload's actions with other electronic warfare
assets.
Phase I: The contractor will develop a top level system concept for the ECM payload. In doing this, the
contractor will analyze existing and planned anti-ship threat missiles and the airborne targeting radars to determine
off-board radiation characteristics necessary to defeat the threat. The contractor will coordinate with the UAV
program office to obtain planned UAV operational characteristics, the limitations on the payloads imposed by the
UAV, and the interface requirements between UAVs and the payloads. The contractor will evaluate relevant
Navy-46
technologies that could be applied to the development of the payload and its command and control. The system
concept will contain a concept of operations and a top level set of technical and interface requirements for the ECM
payload. The system concept will be documented in the form of a final report for Phase I.
Phase II: A feasibility study will be performed to identify key technology issues and a set of technology
demonstrations will be designed and conducted to support initialization of a follow-on ECM payload advanced
development program.
N92-169 TITLE: Target Aim Point Selection Based on Real Time Optical Processing Visual or Infrared Generated
Scenes
CATEGORY: Exploratory Development
OBJECTIVE: Develop and demonstrate an optical processing system capable of unambiguously recognizing target
features from two dimensional visual or thermal generated images in real-time.
DESCRIPTION: Future weapon system may have to incorporate multimedia sensors or seekers to overcome
various enemy countermeasure techniques. For example an anti-radiation missile could be rendered ineffective if the
enemy turned of their active RF emitters during the terminal homing phase. To circumvent this tactic, future weapon
systems may have to incorporate visual or thermal imaging systems along with radiation homing to track and
destroy the target. These imaging systems typically have difficulty processing target information where the target is
changing aspect or perspective or is occluded, let alone finding a designated aim-point. Optical processing systems,
owing to their inherent speed and two dimensional image processing capability can potentially overcome the
problems of processing rapidly changing, cluttered data from imaging sensors and performing aim point selection in
real time. What is needed is a new and innovative approach to the design of an optical correlator system capable of
inputting infra-red or video generated scenes and extracting and recognizing selected target features in the presence
of clutter, noise or obstructions. Phase I should consist of the development of the theory, mathematical basis and
algorithms and an optical architecture concept. Some limited optical bench demonstration of some features of the
design is desirable. Phase II should result in the detailed design, test, demonstration and delivery of a working
prototype system, including all optics, lasers, input/output interfaces, post processors, and special devices, such as
spatial light modulators, assembled on a compact, easily transportable base.
Phase I: Development of theory, algorithms, architecture and limited demonstration of key concepts.
Phase II: Design, development, demonstration and delivery of prototype system.
NAVAL AIR DEVELOPMENT CENTER
N92-170 TITLE: LADAR Identification (ID) Demonstration
CATEGORY: Exploratory Development
OBJECTIVE: To demonstrate the feasibility of identifying non-cooperative airborne targets using LADAR.
DESCRIPTION: Future Navy platforms need a means to positively identify non-cooperative airborne targets for
fleet defense (See Reference). Current advances in compact, high power, and stable CO2 LASERS show promise
in achieving this objective. The Laser Radar (LADAR) system operates by briefly illuminating the unknown
aircraft and then extracting the doppler shifted return which contains aircraft type unique information that will
provide positive identification.
This SBIR effort will demonstrate LADAR technology by devising an innovative method of performing a long
range (>50nmi), real time, ground to air demonstration using a suitable CO2 LADAR and optical tracking system.
The LADAR shall meet the following minimum requirements: (a) Maximum volume = 3 ft3, (b) Minimum power
= 75 watts, CW, (c) Laser stability = + 20 kHz over 1msec and + 1MHz over 1 sec and (d) Maximum weight = 200
lbs.
Phase I: Program would include the integration design and the development of the real time demonstration
plan.
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Phase II: Would proceed upon the approval of Phase I design and demonstration plan and will perform the
actual LADAR ID technology demonstration.
N92-171 TITLE: Detection of Thermal Damage in Composite Materials
CATEGORY: Exploratory Development
OBJECTIVE: To develop a method for detecting and assessing critical heat damage in advanced fiber reinforced
organic matrix composites, such as graphite/epoxy laminates.
DESCRIPTION: Composite structural components used in aircraft applications can potentially be exposed to
thermal environments which could cause them to exceed their glass transition temperature. As a result, matrix
cracking, delamination, fiber debonding and permanent reduction in glass transition temperature may occur. These
conditions could result in loss of structural load carrying capacity. Examples of such exposure might be jet blasts or
accidental exposure to fire. There are currently no techniques available that are known to reliably detect such
damage prior to loss in material properties. In addition, there are no analytical methods for assessing the effect of
any such damage on future material performance.
Phase I: Develop a method for quantifying the degree of thermal damage in a composite.
Phase II: Using the technique and laboratory specimens, develop a methodology to quantify loss in
mechanical properties resulting from heat damage.
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N92-172 TITLE: Aircraft Target Identification in an ECM Environment
CATEGORY: Exploratory Development
OBJECTIVE: To develop aircraft target identification techniques that can be used in the presence of ECM.
DESCRIPTION: Positive target identification of airborne targets is a high priority for the Department of Defense.
Radar is the primary long range sensor for airborne, ground based and shipboard weapons control systems and is
presently used for target identification. Since target identification relies on the radar return signal, ECM which
exploits the radar return may effect target identification. The effects of all ECM techniques should be investigated
and performance expectations should be predicted. Target identification generally requires signal processing
beyond radar signal processing therefore in very sophisticated ECM, the target identification process may provide
the radar with information that is normally not available. These cases should be identified and possible ECCM
should be investigated. Algorithms should be developed and implemented for both ECM and ECCM target
identification operation.
Phase I: Should consist of a study detailing the approach to be undertaken to obtain the requirements above.
The expected results should be detailed and the test and evaluation requirements should be discussed.
Phase II: Consists of analyzing the performance of operational and developmental radar target identification
techniques in the presence of various ECM. Performance predictions and solutions to problems should be made.
Algorithms should be developed and ECM/ECCM target identification demonstrations should be performed with
operational radar systems.
N92-173 TITLE: Active Control of Fighter Maneuvers
CATEGORY: Exploratory Development
OBJECTIVE: To design multivariable flight control systems that actively control fighter maneuvers in order to
enhance ride quality and suppress vibrations. The superiority of such active control designs need to be
demonstrated with application to the Navy F/A-18A fighter.
DESCRIPTION: Recent trend is to move away from fighters designed for specialized missions to fighters which
adapt to a variety of missions, such as close air-to-air combat, low level flying, etc. In these situations, it is
important that the aircraft be highly maneuverable with quick response to controls. The fighter can benefit a great
deal if provision is made to actively control for ride maneuver control, load alleviation, structural vibration control,
etc. Since active control in such cases requires multiple control surfaces, multivariable methods are ideally suited
for the active control of aircraft maneuvers. The latest H-infinity control techniques are particularly promising for
such applications because of the presence of uncertainties and model variations.
Phase I: The SBIR should involve a clear problem formulation and definition of the control strategy and
working out proof of concept in various maneuvers for the six degree of freedom model of an F/A-18A aircraft.
Phase II: Involve a feasibility demonstration of the control strategies via simulation and testing.
N92-174 TITLE: Fuzzy Logic Applications to Flight Control
CATEGORY: Exploratory Development
OBJECTIVE: To develop and demonstrate (via simulation) a flight control architecture that utilizes fuzzy logic
technology to significantly enhance the performance of a representative high performance aircraft.
DESCRIPTION: Fuzzy logic based control has become the first machine intelligence technology to see wide use in
real products such as auto-focusing and heating control systems. The purpose of this project is to identify a specific
area where fuzzy logic may provide unique advantages to the flight control of a high performance jet aircraft. The
aircraft model used for this research should exhibit both static and dynamic instabilities and uncertainties in its plant
dynamics. The proposed controller may be a pure fuzzy logic controller or it may be integrated with a more
conventional controller (i.e. fuzzy augmentation system, fuzzy gain scheduler, etc.). The proposed controller may
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perform inner loop tasks such as primary command and stability augmentation or it may perform outer loop tasks
such as automated trajectory control for weapons delivery or terrain following/terrain avoidance. For the inner loop
control task, it must provide acceptable pilot handling qualities. In all cases, it must be sensitive to real-world
implementation issues, such as validation and computational overhead.
Phase I: Should consist of a simulation using a reduced order linear model of a high performance aircraft and
the candidate fuzzy logic system which will be sufficient to demonstrate an initial proof of concept. The
accompanying study should utilize data from the simulation to identify and, if possible, quantify the expected
advantages of the candidate system over current systems in terms of performance, cost, etc.
Phase II: Should consist of a high fidelity simulation of the fuzzy logic controller concept developed in Phase
I. The simulation should include, as a minimum, a six degree of freedom (6-DOF) non-linear version of the high
performance aircraft model used in Phase I with accurate sensor, actuator and atmospheric disturbance models.
This effort should address in detail, the solutions to any problems identified in Phase I along with implementation
considerations such as specialized hardware/software and validation requirements of the system.
NAVAL AIR ENGINEERING CENTER
N92-175 TITLE: Disposal of Chlorofluorocarbon (CFC) Substances
CATEGORY: Exploratory Development
OBJECTIVE: Investigate and identify cost effective processes for disposing of Chlorofluorocarbon (CFC)
substances that are stratospheric Ozone Depleting Substances (ODS).
DESCRIPTION: At present, the U.S. Navy has several million pounds of CFC substances which are known to be
ODS in use as refrigerants, fire extinguishants and solvents. If drop-in replacements or alternatives were found in
the near future, it would be necessary to dispose of the ozone depleters. Present methods of disposal (incineration)
are estimated to be $10.00 to $25.00 per pound and produce toxic by-products. Alternative disposal technology that
is more cost effective and cleaner, needs to be identified as soon as possible.
Phase I: Should produce a report detailing a process or processes that will provide for the cost effective
disposal of CFC substances used in the U.S. Navy. The report should address in detail the anticipated cost,
technology to be used, analysis of chemical reactions and the by-products of destruction. It shall also describe the
ultimate disposal of all by-products and any special procedures that may be required. It shall describe in detail the
procedures for disposing of any toxic by-products.
Phase II: The contractor shall demonstrate the feasibility of using the process or processes for disposing of
ODS identified during Phase I. It shall include the actual demonstration of destruction of a small batch of substance
and the handling and disposal of the resulting by-products. It shall also include an analysis that details the cost and
problems of expanding the demonstrated process or processes to a full scale operation.
NAVAL AIR PROPULSION CENTER
N92-176 TITLE: Innovative, Lightweight, and Simple Air Filtration Concepts for Small Displacement Diesel
Engines
CATEGORY: Exploratory Development
OBJECTIVE: To develop a simple lightweight air filtration system featuring a lower pressure drop across the
element than conventional paper and foam elements.
DESCRIPTION: The Navy is developing lightweight diesel engines for use in unmanned aerial vehicles (UAVs).
The UAVs operate in environments that require intake air to be filtered to trap airborne contaminants before they
can damage engine internals. These naturally aspirated engines operate at low airflows and any decrease in intake
air pressure will result in an undesirable power loss. For this reason, the Navy would like to investigate simple
lightweight filtering methods that would produce negligible or no pressure drop across the engine intake. The
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engines have output in the 25 to 100 HP range and have airflows less than or equal to 1.0 lb/sec (at standard
conditions). Desired filtration is 60 mesh.
Phase I: It is anticipated that investigation into candidate concepts would be divided into two phases. Phase I
would generate conceptual designs which would be validated through theory and analytical assessment and/or
testing.
Phase II: Based on successful results in Phase I, Phase II would consist of fabrication of proof of concept
designs and experimental verification of the approach.
N92-177 TITLE: Innovative Unconventional Small Engine Concepts
CATEGORY: Exploratory Development
OBJECTIVE: To develop an innovative unconventional small engine concept.
DESCRIPTION: The Navy wishes to explore concepts in unconventional diesel fueled propulsion systems for use
for unmanned air vehicles. The concepts desired shall exclude the use of pistons, rotors (wankel type engines),
lever arm mechanisms and conventional aerodynamic turbine components. Please note the use of unconventional
materials does not constitute an unconventional engine concept. The general category of engine should be one of a
50-horsepower capacity which can either be modularized or scaled to 250 horsepower, potential power density after
development should be 1 horsepower per pound or better and bsfc at 70 percent of maximum power should be 0.5
lb per horsepower hour.
Phase I would generate conceptual designs which would be validated through theory and subscale prototype
testing. Based on successful results in Phase I, Phase II would consist of fabrication of full scale proof of
concept designs and experimental verification of the approach.
N92-178 TITLE: Innovative Concepts for Directly Meaduring Airflow in Intermittent Combustion Engines
CATEGORY: Exploratory Development
OBJECTIVE: To develop a direct method for accurately measuring airflow into an Intermittent Combustion engine
that does not interfere with the flow.
DESCRIPTION: The Navy is developing lightweight diesel engines for use in unmanned aerial vehicles (UAVs)
which operate on both the two and the four stroke cycle. The engines are designed to operate at altitudes in the
range of sea level to 40K feet. During engine testing, it is desirable to accurately measure airflow to determine
volumetric efficiency, specific air consumption, and the air fuel ratio. It is understood that any appreciable pressure
drop across the airflow measuring device will have an undesirable effect on engine performance. It should also be
noted that the engine airflow is not steady, but pulsating. Venturi effects have a pressure drop associated with them
and are not available with enough accuracy in the large turndown range required to test these engines in the altitude
range described above. Positive displacement measurement from a gas holder is accurate but bulky and
cumbersome. A plenum chamber with an orifice needs to be very large to be accurate and produces a significant
pressure drop. Other problems associated with directly measuring airflow may be found in the SAE Technical
paper 890242, entitled Airflow Measurement in Internal Combustion Engines by C. R. Stone. For these reasons, the
Navy would like to investigate innovative concepts for directly measuring airflow into internal combustion engines
in the 25 to 100 HP range, with associated airflows up to 1.0 1b/sec.
The immediate objective of this program is ground test cell use. However, systems usable for lightweight in-
flight advanced engine control usage would have additional merit.
Phase I would generate conceptual designs which would be validated through theory and testing of a subscale
system.
Based on successful results in Phase I, Phase II would consist of fabrication of proof of concept designs and
experimental full scale verification of the approach.
N92-179 TITLE: Engine Control Via a Standard 1553 Bus Controller for Use at Engine Test Facilities
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CATEGORY: Engineering Development
OBJECTIVE: Provide for the definition and development of a standard 1553 Bus Controller for use with current
and future air propulsion systems. An economical and efficient means of interfacing to the FADECs used with the
various engines in the Navy inventory is sought.
DESCRIPTION: Engines developed for the Navy are equipped with FADECs containing a 1553 Bus interface. All
future engines are expected to be so equipped. At present, either the engine manufacture provides the engine test
facility with a controller unit, or the test facility must purchase or rent a controller identical to the one used by the
manufacturer. As more engines are developed and manufactured with FADECs outfitted with 1553 Bus interfaces,
this method of providing for bus controllers becomes more cumbersome, inadequate, and costly, since the Navy is
faced with the need to support a multitude of controllers. The bus controller should be tailored for control room use
at engine test facilities. Interface to the engine operator panel should remain consistent from test to test. Real time
display of parameters should be developed. A reliable interface to the facility main frame computer should be
established which will allow quick turn around time of data. Engines utilizing FADECs which require 1553 bus
Controllers will ultimately be rebuilt and tested at NARFS. These facilities will be faced with the need to obtain bus
controllers. The standard 1553 Bus controllers developed for NAPC would find direct application at these facilities.
Phase I: The first phase of the research is to conclude a feasibility study. The study will: 1) analyze hardware
and software requirements; and 2) complete a detailed proposal for a prototype standard 1553 Bus controller. The
concept must allow for configuration by the user, interface to control room displays and inputs, and communication
of information to a main frame computer in real time. Event recording with play back capability is also required.
Phase II: The prototype defined in phase I is to be constructed and tested to preset guidelines. The test will
determine the effectiveness of the proposed methodology under
NAPC specified conditions. The prototype demonstration will include validation of the concept under actual test
conditions.
NAVAL AIR TEST CENTER
N92-180 TITLE: Anechoic Chamber Radiated Environment
CATEGORY: Exploratory Development
OBJECTIVE: To design and install a low-cost, wide-band radio frequency (rf) radiated environment to be
permanently installed in the rf shielded walls of anechoic chambers. This capability will permit "quick look" tests
where fine direction of arrival is not required.
DESCRIPTION: When an installed electronic system which needs rf stimulation is placed in an anechoic chamber,
three primary means of providing a signal environment are utilized: accurate, but time-consuming
behind-the-antenna, utilizing directional couplers, radiated environment from antennas temporarily mounted on
tripods, or extremely expensive in-wall antenna arrays and/or turntables. The anechoic chamber radiated
environment capability proposed would provide an extremely rapid, yet low-cost means of testing installed systems.
Phase I: Design of specialized antennas and/or the methodology for installing off-the-shelf antennas in the
shielded chamber walls without compromising shielding effectiveness or anechoic performance. A concurrent
effort would be the design of moveable proof-of-concept "billboard" arrays containing high power broadband
amplifiers and high-speed rf switching networks, under computer control, to provide a limited but polarization and
spatially diverse, radiated RF environment. These billboards would be capable of interfacing with the Tactical
Electronic Warfare Environment Simulator (TEWES) or other source of simulated radar and/or communications
type signals to provide a realistic radiated threat environment from a limited azimuth and elevation sector.
Phase II: Would develop and demonstrate two moveable proof-of-concept billboard arrays containing high
power broadband amplifiers and high-speed switching networks to provide a wide-band, polarization diverse,
limited resolution radiated environment. This phase will also include the development of a interface between the
Advanced TEWES and the billboard arrays and provide the Initial Operating Capability (IOC) of a low-cost
Anechoic Chamber Radiated Environment.
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N92-181 TITLE: Wireless Airborne Instrumentation System
CATEGORY: Exploratory Research
OBJECTIVE: Develop small, self-contained transmitter modules and a receiver module which will allow the
transmission of transducer data from a remote part of a test aircraft or missile to a central acquisition system without
the need for connecting hard wiring. Modules operating on internal power, able to handle multiple local
transducers, and able to withstand the environment of a modern jet fighter aircraft are required.
DESCRIPTION: About half of the cost of modern flight test instrumentation system installations results from the
need to run instrumentation wiring throughout the aircraft to connect the various transducers to a central data
acquisition system and to provide the transducers with the necessary electrical power. Elimination of this
requirement would result in significant savings in flight test program cost, and in the time required to complete the
installation.
Phase I: Provide a specification of the basic system requirements, identify any needed testing required to
establish the ability of likely equipment to withstand the complete operating environment of such a system and to
provide the required performance, and identify potential equipment, either currently available or to be developed,
that could be used to meet these requirements.
Phase II: Develop a prototype transmitter and receiver unit and provide laboratory testing to demonstrate that
this system can provide the required operating performance. If development progress will allow a flight evaluation
of the equipment, make the prototype available for Navy flight evaluation. Such a prototype system would not have
to provide the full multiple-channel capability nor operating endurance suitable for a production system, but should
demonstrate the feasibility of the approach.
N93-182 TITLE: Infrared Optical Fibers
CATEGORY: Engineering Development
OBJECTIVE: To develop optical fibers capable of relaying high quality infrared (IR) images over distances of 100
to 150 feet in the 3-5 and 8-12 micron regions. If successful, the optical fibers developed will be integrated into the
Offensive Sensors Laboratory IR Scene Generation System that is currently under design.
DESCRIPTION: Current optical fibers relay information using visible light or lasers. The purpose of this project is
to determine if optical fibers capable of relaying high quality IR images can be developed and produced at a
reasonable cost. The optical fibers should be able to handle IR transmissions in the 3-12 micron range over
distances of 100 to 150 feet with minimal loss. If the full range of wavelengths is not possible, the fibers must be
able to handle IR transmissions in the 3-5 and 8-12 micron regions. The fibers must be able to handle coherent
imaging and diffraction limited images. The fibers must be capable of working with a focal attachments at either
end of the fibers, preferably attached to the fibers or with the maximum numerical aperture bundles at one end of
the fibers. If possible, the fibers should emulate atmospheric transmission in the 3-12 micron region.
Phase I: Should consist of a study outlining the approach which will be undertaken to pursue the requirements
addressed above with sufficient data to demonstrate feasibility.
Phase II: Should use the approach outlined in Phase I to produce two optical fibers 100 feet in length and two
optical fibers 150 feet in length and deliver them to the government for testing.
N92-183 TITLE: Artificial Intelligence (AI) Technology to Enhance Flight Test Software Configuration Control
CATEGORY: Exploratory Development
OBJECTIVE: Use AI technology to develop a program that can determine the parametric effects of software
changes to specified configurations during flight testing.
DESCRIPTION: Testing a modern rotorcraft operational flight trainer (OFT), weapon systems trainer (WST), or
rotorcraft digital flight control system involves numerous software changes by the contractor. The government test
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team tries to maintain configuration control, testing a "frozen" configuration. The contractor may say that he/she
can make a half dozen software corrections in 5 min without affecting any of the previous testing. Considerable
cross-coupling exists in helicopter flight characteristics, and trade-offs exist between testing a frozen configuration
and in making software changes to enhance the configuration. The purpose of this project is to develop a program
that can analyze flight trainer or digital flight control system block diagrams, prints, etc., and perturb the system,
and determine the parametric effects of software configuration changes.
Phase I: Review software configuration control during typical Navy flight trainer acceptance testing, and
software configuration control during rotorcraft digital flight control system testing. Develop a plan for a program,
using AI technology, to help the test team enhance configuration control.
Phase II: Use the approach documented in Phase I to develop the AI technology configuration control
enhancement software. Demonstrate and support testing the AI software in conjunction with a specified Navy flight
trainer test program and digital flight control test program. Correct problems and incorporate recommended
changes resulting from the initial tests. Deliver final product, with appropriate documentation, to the Navy.
NAVAL WEAPONS CENTER
N92-184 TITLE: Radiation Heat Transfer Analysis
CATEGORY: Advanced Development
OBJECTIVE: To develop a computer software package that provides solutions to radiant energy exchange in
enclosures over multiple wavelength bands and with participating media. In addition, the software would integrate
this radiant energy exchange analysis capability with the pre- and postprocessing capabilities of the MOVIESTAR
computer program to build a heat transfer model and interface with general thermal analyzers such as SINDA,
TMG, and ABAQUS which predict thermal response of the system.
DESCRIPTION: The purpose of this project is to provide Navy engineers with an economical alternative to leasing
proprietary radiation heat transfer analysis software such as those obtainable in commercial software packages.
Existing radiant energy exchange analysis software that determines radiation viewfactors in multiple enclosures
could be modified to interface with the MOVIESTAR and ABAQUS as part of a Phase I effort to demonstrate
feasibility.
Phase II: Should use the approach demonstrated in Phase I to interface with additional general thermal
analyzers (e.g. SINDA, TMG, etc) and to develop radiation analysis software that provides multiple wavelength
band radiation modeling and that includes participating media.
N92-185 TITLE: Improved Thermal Neutron Imaging Method
CATEGORY: Exploratory Development
OBJECTIVE: Develop an improved method of imaging thermal neutrons in real-time or near real-time, suitable for
use in (or as) an electronic neutron radiography imaging system.
DESCRIPTION: A new family of accelerators provides the opportunity for neutron radiography to move from the
reactor based systems to a more attractive accelerator system that can offer portability and turn-key operation
without the hazards of the reactor. An improved method of imaging thermal neutrons that will be provided by the
new accelerator family that has a 106 n/cm2/sec thermal flux, length/diameter ratio of 25, with a desired 12 inch x
12 inch image size. These parameters are approximate and there are some additional unknowns that will be
established when the solicitation is released. The component or system will be used to image dynamic events in
addition to the traditional static test item neutron radiography. The primary parameters for improvement should be
signal to noise ratio, spatial resolution, and contrast sensitivity.
Phase I: Evaluate present thermal neutron imaging systems and neutron detectors and compare them to the
proposed method. Demonstrate a sub-scale system or component for a proof of concept with a final report.
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Phase II: Fabricate a prototype system or component that will fit into a commercially available system with
the intention of marketing the developed item.
N92-186 TITLE: Laser Beam Steering Via the Pockels Effect
CATEGORY: Exploratory Development
OBJECTIVE: Build a low cost, laser beam steering device which can change beam direction at GHz frequencies.
Applications include components for hybrid optical computers and laser radar.
DESCRIPTION: Nonlinear optical polymers (NLOP) offer an excellent opportunity for fabricating low cost
electro-optical waveguides for GHz phase modulation. An electro-optical waveguide consists of a layer of
nonlinear optical polymer (NLOP) sandwiched between transparent buffer polymer and electrodes. When an
electrical field is applied across a portion of the NLOP, the index of refraction of the NLOP is changed. This
change is due to p-electron shifts which occur in less than a picosecond. State-of-the-art NLOP require several
centimeters of interaction length to achieve 2p phase change at acceptable modulation voltages.5 Hence, to steer a
laser beam over wide angles, a novel device configuration is required, for example, one involving an array of NLOP
waveguides, fabricated by microlithography. Successful proposals will include a detailed drawing of a novel beam
steering device. Serious consideration will only be given to investigators experienced in fabricating optical
waveguides.
Phase I: The expected deliverable will be a report outlining the approach and providing performance data on
prototype materials, e.g., optical rotation in NLOP as a function of the applied electric field. The NLOP should
exhibit an effective c(2) coefficient greater than 30 pm/V and attenuate less than 3 dB/cm at the wavelength of
interest (e.g., 532 nm or greater). Any source of NLOP is acceptable. The NLOP may also be provided by the
Naval Preparing Activity (Naval Weapons Center, China Lake, CA,).
Phase II: Expected deliverable will be a breadboard laser beam deflector. Investigators at the Naval Weapons
Center at China Lake, CA, will be responsible for verifying the optical testing and performance results.
PACIFIC MISSILE TEST CENTER
N92-187 TITLE: Dual Mode Infrared (IR)/Millimeter Wave (MMW) Measurement System
CATEGORY: Engineering Development
OBJECTIVE: To design, fabricate, test and deliver a dual mode IR/MMW sensor measurement system for air-to-
air and air-to-ground measurements of military targets. The system shall be capable of airborne operation in the
Pacific Missile Test Center Airborne Turret IR Measurement System (ATIMS) or ground operation from remote
sites.
DESCRIPTION: Dual mode IR/MMW weapons systems are now under development within the DoD. A need
exists to make target signature measurements in these two bands simultaneously.
An airborne measurement system which operates simultaneously in the 3-5 and 8-12 micrometer bands of the IR
and 35 and 94 gigahertz bands of the MMW is required. The IR portion of the system shall be a high resolution,
passive imager. The MMW portion of the system shall be active and provide range versus line of sight data. The
IR and MMW data shall be in a format of recording on an airborne wide band data tape recorder or video tape
recorder. The IR and MMW data must be tagged so that they can be registered during data reduction.
Phase I: A concept for the system will be developed and the engineering design will be completed. The
deliverable will be a final report.
Phase II: The systems will be fabricated, tested and delivered to the Pacific Missile Test Center. The
deliverables will be the system hardware, a drawing package and an operating/
maintenance manual.
N92-188 TITLE: Multi-Spectral Scene Generation for Hardware-in-the-loop (HWIL) Laboratories
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CATEGORY: Exploratory Development
OBJECTIVE: To design and develop a target screen for multi-spectral HWIL laboratories which is reflective in the
infrared (IR) region and transmissive in the microwave region.
DESCRIPTION: Dual mode missile systems are under development in all three services. Complete test and
evaluation of these very complex systems requires the use of realistic dual mode HWIL laboratories. Such
laboratories are envisioned as being radio frequency (RF) chambers with an array of RF sources on one wall and the
missile under test located at the opposite end of the laboratory. The missile guidance systems will be mounted in a
multi-axis angular motion simulator.
The target screen will be placed between the RF source array and the missile under test. IR sources, mounted
near the missile under test, will project an IR scene onto the screen which will reflect it to the missile. The IR and
RF images will be registered providing a dual mode RF/IR target scene.
Phase I: A concept for an IR reflecting/RF transmitting screen will be developed and fully analyzed. The
deliverable will be a final report describing the screen concept and estimating its capabilities.
Phase II: The screen will be fabricated, tested and delivered to the Pacific Missile Test Center. The
deliverables will be the screen hardware and a report describing its technical parameters and test results.
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